System and method of operating a bleed air system for power recovery of an aircraft engine

Abstract

Systems for power recovery for aircraft engines and methods of operating a bleed air system are disclosed. An exemplary power recovery system (202) for an aircraft engine (110) includes a power recovery turbine (250) coupled to a shaft drive (204). Bleed air valves (534, 536, 538) are coupled between the power recovery turbine (250) and a source of bleed air (242, 244). A controller (500) is configured to operate the bleed air valves (534, 536, 538) to allow a flow of bleed air to the power recovery turbine (250) when the aircraft engine (110) is operated in a predetermined mode of operation.

Description

Technical Field

[0001] This disclosure generally relates to aircraft, and more specifically to engine bleed air power recovery systems and related methods. Background Technology

[0002] Commercial aircraft typically draw bleed air from the compressors in their engines to provide pressurized air for various aircraft systems. For example, commercial aircraft often use bleed air to supply air to environmental control systems to pressurize the aircraft cabin, and / or to provide heated air for anti-icing applications using thermal anti-icing systems. Summary of the Invention

[0003] An exemplary power recovery system for an aircraft engine includes a power recovery turbine coupled to a shaft drive. A bleed air valve is coupled between the power recovery turbine and a bleed air source. A controller is configured to operate the bleed air valve to allow bleed air flow to the power recovery turbine when the aircraft engine is operating in a predetermined operating mode.

[0004] Another exemplary power recovery system includes a power recovery turbine having: a bleed air inlet for receiving bleed air from a bleed air source; a bleed air outlet for providing bleed air to a downstream system; and an output shaft operatively coupled to an input shaft of a shaft drive. The power recovery turbine generates power in response to processing the bleed air as it flows from the bleed air inlet to the bleed air outlet, and transmits the generated power to the input shaft via the output shaft.

[0005] An exemplary aircraft includes an aircraft engine having a core compressor for generating compressed air and a core turbine for driving the core compressor. A power recovery turbine is operatively coupled to the aircraft engine. The power recovery turbine has a turbine inlet in fluid communication with a bleed air supply source provided by the core compressor and a turbine outlet in fluid communication with downstream systems of the aircraft. The power recovery turbine generates power while processing bleed air from the turbine inlet to the turbine outlet and delivers the generated power to the core compressor of the aircraft engine.

[0006] The features, functions, and advantages already discussed can be implemented independently in various embodiments or combined in other embodiments, further details of which can be seen in the following description and figures. Attached Figure Description

[0007] Figure 1 This is an illustration of an exemplary aircraft that includes an exemplary bleed air system having an exemplary power recovery system constructed in accordance with the teachings of this disclosure.

[0008] Figure 2 This is a schematic diagram of an exemplary aircraft engine having the exemplary power recovery system disclosed herein.

[0009] Figure 3 yes Figure 2 A schematic diagram of an exemplary transmission for an exemplary energy recovery system is shown.

[0010] Figure 4 yes Figure 3 A schematic diagram of an exemplary clutch of an exemplary transmission shown.

[0011] Figure 5 yes Figures 1 to 4 A schematic diagram of an exemplary air intake system is shown.

[0012] Figures 6 to 11 It is displayed in different operating modes. Figures 1 to 5 A schematic diagram of an exemplary air intake system is shown.

[0013] Figure 12 Is adopted Figures 1 to 11 The diagram shows an exemplary aircraft engine serving as a starter for an exemplary power recovery system.

[0014] Figure 13 This is a schematic diagram of an exemplary aircraft engine having another exemplary power recovery system disclosed herein.

[0015] Figure 14 It means that it can be generated by Figures 1 to 13 A flowchart illustrating an exemplary method performed by the exemplary bleed air system shown.

[0016] Figure 15 This is a block diagram of an exemplary processing platform configured to perform... Figure 14 The instructions shown are for implementing Figures 1 to 13 An exemplary bleed air system controller for the exemplary bleed air system shown.

[0017] Where possible, the same drawing numbers are used throughout the drawings and the accompanying written description to refer to the same or similar parts. As used in this patent, a statement that any part (e.g., layer, film, region, or plate) is positioned on (e.g., positioned on, placed on, arranged on, or formed on, etc.) another part means that the referenced part is either in contact with the other part or is situated on top of the other part, and one or more intermediate parts are situated between them. A statement that any part is in contact with another part means that there is no intermediate part between the two parts. Detailed Implementation

[0018] Bleed air pressure varies considerably with aircraft operating conditions, such as engine speed and operating altitude. To meet the pressure and / or temperature requirements of various aircraft systems, bleed air is typically extracted from a compressor stage that provides bleed air with pressures and / or temperatures higher than those required by the systems utilizing it. Therefore, before being supplied to aircraft systems (e.g., environmental control systems), the pressurized bleed air is typically cooled via a heat exchanger or precooler and its pressure reduced via a pressure regulating valve. Thus, existing aircraft bleed air systems utilize pressure regulating valves and heat exchangers to reduce the bleed air to permissible pressures and temperatures compatible with the supplied systems. The regulating valve effectively limits the bleed air pressure but does not recover energy from it. Therefore, when cooling the bleed air and / or reducing its pressure for use in various systems, a significant portion of the energy expended by the engine to generate the bleed air is wasted, and thus, extracting bleed air in this manner reduces engine efficiency. This wasted energy leads to greater fuel consumption.

[0019] The exemplary engine bleed air power recovery system and related methods disclosed herein provide compressed or pressurized air to various systems of an aircraft, such as environmental control systems (ECS), thermal anti-icing systems (e.g., wing and / or engine anti-icing systems), pneumatic supply systems (to supply pneumatic devices), and / or any other system of the aircraft that requires the use of compressed air.

[0020] Specifically, the exemplary bleed air recovery system and related methods disclosed herein harvest energy from extracted engine bleed air. The exemplary bleed air recovery system and related methods disclosed herein convert the energy harvested in the bleed air into shaft horsepower, which is fed back into the aircraft engine (e.g., a jet engine high-spool valve shaft). When activated, the exemplary bleed air recovery system and related methods disclosed herein can be used to supplement the power generated by the aircraft's core gas turbine engine (e.g., an aircraft engine). The recovered energy improves the fuel efficiency of the aircraft engine while also increasing the available thrust.

[0021] To harvest energy from bleed air, the bleed air recovery systems and related methods disclosed herein employ a turbine that receives bleed air from the aircraft engine before supplying it to downstream systems (e.g., precoolers, ECS, etc.). For example, the exemplary bleed air recovery systems and related methods disclosed herein can extract bleed air for driving a turbine (e.g., a power recovery turbine) during aircraft engine operation. The exemplary turbines disclosed herein reduce one or more parameters (e.g., pressure, temperature, etc.) of the bleed air before supplying it to downstream systems.

[0022] In some examples, the exemplary bleed air recovery systems and related methods disclosed herein may be employed during predetermined operating modes of the aircraft (e.g., taxiing, takeoff, climb, cruise, landing, etc.). In some examples, to activate and / or deactivate exemplary turbines, the exemplary bleed air recovery systems and related methods disclosed herein may include exemplary control systems to control the flow of bleed air to the turbine. The exemplary control systems disclosed herein include a bleed air valve coupled between a bleed air source and a turbine, and a controller coupled to the bleed air valve (e.g., communicatively and / or operatively). The control system, for example via the controller, may be configured to operate the bleed air valve during predetermined operating modes (e.g., takeoff, climb, descent, landing, cruise, etc.) to direct or direct bleed air from the bleed air supply source to the turbine.

[0023] In some examples, the exemplary bleed air recovery systems and related methods disclosed herein can be used to start aircraft engines. Therefore, in some cases, the starter for an aircraft engine can be replaced by the exemplary bleed air recovery systems and related methods disclosed herein. Specifically, an exemplary turbine can be used to start (e.g., rotate) an aircraft engine. For example, the turbine (e.g., a pneumatic starter turbine) can be configured to generate sufficient starting torque to start the aircraft engine.

[0024] Figure 1 An exemplary aircraft 100 embodying aspects of the teachings of this disclosure is shown. The aircraft 100 includes a fuselage 102, a first wing 104 coupled to the fuselage 102, and a second wing 106 coupled to the fuselage 102. The fuselage 102 defines a cabin 108 for carrying passengers and / or cargo. In the example shown, the aircraft 100 includes an aircraft engine 110 carried by the wing 104 and an aircraft engine 112 carried by the second wing 106. In other examples, the aircraft 100 may include only one engine, or may include two or more engines. The engines may be mounted on the wings 104, 106, and / or on another structure on the aircraft 100 (e.g., at the tail of the fuselage 102).

[0025] Figure 2 yes Figure 1 A partial cross-sectional view of an aircraft engine 110 is shown. The aircraft engine 110 has an exemplary bleed air system 200, which includes a power recovery system 202 according to the teachings of this disclosure. The power recovery system 202 is configured to recover energy from the bleed air and convert the recovered energy into power (e.g., horsepower) delivered to the aircraft engine 110. The energy recovered by the power recovery system 202 improves the fuel efficiency of the aircraft engine 110 while also increasing thrust. In some examples, the energy extracted by the power recovery system 202 may be used for operating (e.g., driving) auxiliary systems (e.g., generators that generate electricity for auxiliary systems or devices such as pumps).

[0026] Figure 2 The power recovery system 202 shown is integrated with aircraft 100 ( Figure 1 The aircraft engine 110 (shown in partial cross-sectional view) is used for implementation. Systems similar to the bleed air system 200 and / or the power recovery system 202 can be combined with the aircraft engine 112 ( Figure 1 This is implemented in a manner that allows for the energy recovery system 202 to be used in various ways. Therefore, in some examples, each of the aircraft engines 110 and 112 includes an energy recovery system 202. In some examples, each of the aircraft engines 110 and 112 employs a dedicated energy recovery system 202. This configuration enables the energy recovery systems 202 of each of the aircraft engines 110 and 112 to work together to meet the supply air requirements of aircraft systems (e.g., ECS, auxiliary aerodynamic systems, etc.) and / or provide redundancy. In some examples, only one of the aircraft engines 110 and 112 includes the energy recovery system 202 disclosed herein. For the sake of brevity, only one aircraft engine 110 will be described in detail.

[0027] Reference Figure 2 The aircraft engine 110 is a turbofan engine having an engine core 204 (sometimes referred to as a gas turbine engine) and a fan 206. The engine core 204 drives the fan 206 to generate thrust. The fan 206 rotates within the engine nacelle 208 of the aircraft engine 110. When the fan 206 rotates, it generates an airflow 210. A portion of the fan air 210a flows through a fan bypass 212 (e.g., a duct, channel, passage, nozzle duct, etc.) that bypasses the engine core 204, and another portion 210b of the airflow 210 is also supplied to the engine core 204 for combustion.

[0028] Engine core 204 operates by drawing in air via fan 206 through compressor intake section 214 of engine compressor 216 (e.g., core compressor) within engine core 204. Engine compressor 216 comprises multiple compressor sections. For example, as shown, engine compressor 216 is a dual-shaft compressor comprising two compressors, a first or low-pressure compressor (LPC) 218 ​​and a second or high-pressure compressor (HPC) 220. In the example shown, LPC 218 provides relatively low-pressure air, while HPC 220 provides relatively high-pressure air. LPC 218 and HPC 220 are operatively coupled to a corresponding low-pressure compressor (LPC) shaft 222 (e.g., first spindle) and high-pressure compressor (HPC) shaft 224 (e.g., second spindle). Turbine 226 (e.g., core turbine) drives fan 206 and engine compressor 216. Specifically, turbine 226 comprises a low-pressure (LP) turbine 228 and a high-pressure (HP) turbine 230. To drive engine compressor 216 and fan 206, LPC shaft 222 is operatively coupled to LP turbine 228, and HPC shaft 224 is operatively coupled to HP turbine 230. Therefore, LPC 218 and HPC 220 are shaft-driven power units. As used herein, a shaft-driven power unit refers to a machine or device capable of absorbing power or receiving energy via an input shaft of a machine. For example, LPC 218 includes LPC shaft 222 (e.g., an input shaft) receiving power from LP turbine 228, and HPC 220 includes HPC shaft 224 (e.g., an input shaft) receiving power from HP turbine 230. Therefore, LPC 218 and HPC are shaft-driven power units or machines capable of receiving power or energy. In some examples, engine compressor 216 may include more or fewer compressor sections, each compressor section having, for example, a turbine and a shaft.

[0029] After exiting HPC 220, high-pressure air is supplied to combustion chamber 232, where fuel is injected, mixed with the high-pressure air, and ignited. The high-energy airflow exiting combustion chamber 232 causes the blades of LP turbine 228 and HP turbine 230 to rotate, which are coupled to one of LPC shaft 222 or HP shaft 224, respectively. The rotation of LPC shaft 222 and HP shaft 224 causes the blades of LPC 218 and HPC 220 to rotate. Heated air is discharged through nozzle 234, where it mixes with cooler fan air 210a supplied by fan 206 and bypasses engine core 204 (e.g., engine core) via fan bypass 212 to generate forward thrust that propels aircraft 100 in a forward direction. Figure 1Although in this example the aircraft engine 110 is implemented as a turbofan engine, the power recovery system 202 can be similarly implemented by combining other types of engines (e.g., turboprop engines, open rotor engines, etc.).

[0030] To supply pressurized air (i.e., compressed air) to various systems of the aircraft 100, the aircraft engine 110 of the example shown includes a bleed air system 200. For example, the bleed air system 200 supplies supply air (e.g., pressurized, cooled, and / or heated air) to various systems including, for example, an environmental control system (ECS) 236, a thermal anti-icing system (TAI) 238 including an engine anti-icing system (EAI) 238a and a wing anti-icing system (WAI) 238b, and / or any other system 240 of the aircraft 100 that utilizes pressurized, cooled, and / or heated air. For example, the ECS 236 regulates the cabin supply air to cabin pressure and / or cabin temperature and supplies the regulated air to the cabin 108 of the fuselage 102 (…). Figure 1 Specifically, the air supplied by ECS 236 is used to pressurize cabin 108 and to provide cooling and / or heating air to regulate the temperature of the air in cabin 108 to a comfortable setting. ECS 236 may include one or more ECS components (e.g., an air recirculation refrigeration system) that receive pressurized air (e.g., pressurized and / or heated air) from bleed air system 200 and regulate or adjust the air to cabin pressure and / or temperature. EAI 238a and WAI 238b respectively utilize the supplied air for de-icing or preventing icing. Figure 1 Ice forms on the outer surfaces of the aircraft engines 110, 112 and wings 104, 106. Supply air can be provided to other systems 240, including, for example, pneumatic systems.

[0031] To provide pressurized supply air, the illustrated bleed air system 200 draws bleed air from the aircraft engine 110. For example, the bleed air system 200 draws bleed air from a dedicated compressor stage (e.g., first stage, second stage, fourth stage, etc.) of the HPC 220. Specifically, bleed air is supplied from the first bleed air port 242 of the HPC 220 (e.g., fourth stage bleed air port) and / or from the second bleed air port 244 of the HPC 220 (e.g., tenth stage bleed air port). In some cases, the bleed air drawn from the HPC 220 may have a pressure between approximately 40 psi and 150 psi and a pressure between approximately 50 psi. o F and 700 oTemperature between F. In some examples, bleed gas system 200 extracts bleed gas from LPC 218 via LP bleed gas port. In some examples, bleed gas system 200 extracts bleed gas from first bleed gas port 242, second bleed gas port 244 and / or other bleed gas ports (i.e., receiving mixed bleed gas from various bleed gas ports and / or compressor stage).

[0032] The power recovery system 202 includes a power recovery (PR) turbine 250 that receives bleed air via turbine inlet 252 (i.e., bleed air inlet) and discharges the bleed air to a precooler 256 (e.g., heat exchanger) via turbine outlet 254 (e.g., bleed air outlet). The precooler 256 receives the bleed air and supplies it to downstream systems (e.g., ECS 236, other systems 240, engine block ducts, etc.). The precooler 256 is configured to receive fan air 210a from fan duct 290 via fan air inlet 292 to extract heat from the bleed air passing through the precooler 256, thereby reducing the temperature of the bleed air. The heated fan air exiting the precooler 256 via fan air outlet 294 is discharged via a tail vent (e.g., and used for thrust recovery).

[0033] Furthermore, the power recovery system 202 extracts or harvests energy from the engine bleed air. Specifically, the PR turbine 250 generates power while processing the bleed air from turbine inlet 252 to turbine outlet 254 and transmits the generated power to the engine compressor 216 of the aircraft engine 110. For example, as the bleed air flows between turbine inlet 252 and turbine outlet 254, the PR turbine 250 extracts or harvests energy by reducing one or more parameters from the bleed air (e.g., temperature, pressure, etc.). In some examples, the power recovery system 202 extracts energy from the bleed air during predetermined operating states of the aircraft 100 (e.g., taxiing, takeoff, climb, cruise, descent, landing, etc.). The energy extracted from the bleed air is converted into power (e.g., shaft horsepower) and transmitted (e.g., fed back) to the aircraft engine 110 via the PR turbine 250. In the example shown, the shaft horsepower is transmitted to the HPC shaft 224 via the PR turbine 250. However, in some examples, the energy extracted by the PR turbine 250 is fed back to the LPC shaft 222.

[0034] To operatively couple the power recovery system 202 and the aircraft engine 110, the aircraft engine 110 employs a transmission 260 (e.g., a fixed-ratio transmission, a continuously variable transmission, etc.). In some examples, the power recovery system 202 and / or the transmission 260 provide means for transferring energy (e.g., horsepower) to the aircraft engine 110. The transmission 260 includes a drive shaft 262 having a first gear 264 (e.g., a bevel gear) that engages (e.g., meshes) with a second gear 266 (e.g., a second bevel gear), the second gear 266 being operatively coupled to the HPC shaft 224 of the HPC 220.

[0035] Figure 3 yes Figure 2 A schematic diagram of an exemplary transmission 260 is shown. The power recovery system 202 is driven by bleed air 302 from the aircraft engine 110. For example, bleed air 302 flows through a PR turbine 250 to a turbine inlet 252 and via a turbine outlet 254 to a precooler 256. The PR turbine 250 converts the energy in the bleed air 302 into power (e.g., shaft horsepower) and transmits that power to the aircraft engine 110. For example, at the turbine inlet 252, the bleed air has one or more first fluid characteristics (e.g., bleed air temperature, bleed air pressure, etc.). At the turbine outlet 254, the bleed air 302 has one or more second fluid characteristics (e.g., bleed air temperature, bleed air pressure, etc.) that are different from (e.g., less than) the first fluid characteristics of the bleed air 302 at the turbine inlet 252. For example, the bleed air 302 has a first pressure and a first temperature at the turbine inlet 252 that are greater than a second pressure and a second temperature at the turbine outlet 254. Therefore, as bleed air 302 flows from turbine inlet 252 to turbine outlet 254 through PR turbine 250, PR turbine 250 reduces the pressure and temperature of bleed air 302. Energy extracted from bleed air 302 (e.g., energy from reducing the temperature and pressure of bleed air 302) is collected or extracted by PR turbine 250. PR turbine 250 outputs energy (e.g., power) via turbine output shaft 304, which is then transmitted to aircraft engine 110 via transmission 260 (e.g., continuously variable transmission). For example, turbine output shaft 304 is operatively coupled to HPC shaft 224 via transmission 260. Transmission 260 is mounted between aircraft engine 110 (e.g., HPC shaft 224) and PR turbine 250.

[0036] The transmission 260 enables the speed of the PR turbine 250 to vary (e.g., increase or decrease) relative to the operating speed of the aircraft engine 110 (e.g., HPC shaft 224). For example, the transmission 260 alters (e.g., increases or decreases) the speed of the PR turbine 250 (e.g., revolutions per minute (RPM)) to match the speed (e.g., revolutions per minute (RPM)) of the HPC shaft 224 of the aircraft engine 110. Specifically, the gearbox 306 matches the RPM of the turbine output shaft 304 and the RPM of the HPC shaft 224 to enable the PR turbine 250 to transmit torque to the HPC shaft 224.

[0037] To change the speed of the turbine output shaft 304, the transmission 260 includes a gearbox 306. For example, gearbox 306 is a reduction gearbox or a multi-speed gearbox. Gearbox 306 is operatively coupled to the PR turbine 250 and the HPC shaft 224. For example, gearbox 306 includes a gearbox input shaft 308, which is operatively coupled to the turbine output shaft 304 via a gear train 310. The gear train 310 of the illustrated example includes a first gear 312 (e.g., a spur gear) and a second gear 314 (e.g., a spur gear) meshing with the first gear 312. The first gear 312 is coupled (e.g., fixed or keyed) to the turbine output shaft 304 such that the first gear 312 rotates together with the turbine output shaft 304. The second gear 314 is coupled (e.g., fixed or keyed) to the gearbox input shaft 308 such that the second gear 314 rotates together with the gearbox input shaft 308. Therefore, rotation of the turbine output shaft 304 causes rotation of the gearbox input shaft 308 via gear train 310 (e.g., first gear 312 and second gear 314). The gearbox input shaft 308, in turn, causes rotation of the gearbox output shaft 316. The gearbox output shaft 316 is coupled to the drive shaft 262. The first gear 264 is coupled (e.g., fixed or keyed) to the drive shaft 262, which engages (e.g., meshes) with a second gear 266, which is operatively coupled (e.g., fixed or keyed) to the HPC shaft 224 of the HPC 220. In the example shown, the first gear 264 and the second gear 266 are oriented substantially perpendicular to each other. When the drive shaft 262 rotates about its longitudinal axis, the first gear 264, engaged with the second gear 266, causes the second gear 266 to rotate, and thus causes the HPC shaft 224 to rotate about its longitudinal axis, thereby transmitting power or energy (e.g., horsepower) to the aircraft engine 110.

[0038] In the example shown, a gear ratio is employed between the HPC shaft 224 and the PR turbine 250 to allow the rotational speed of the drive shaft 262 to match (e.g., match RPM) the rotational speed of the HPC shaft 224. For example, gearbox 306 changes (e.g., increases or decreases) the rotational speed of gearbox input shaft 308 based on the gear ratio of the first gear 264 and the second gear 266 (e.g., a 2:1 ratio, a 1:1 ratio, etc.) to provide a rotational speed of gearbox output shaft 316 that matches the rotational speed of the HPC shaft 224. Therefore, turbine output shaft 304 rotates to provide power (e.g., horsepower) to HPC shaft 224 via transmission 260 (e.g., gearbox 306).

[0039] To engage and / or disengage the transmission 260 from the HPC shaft 224, the transmission 260 includes a clutch 318. The clutch 318 moves between an engaged position that rotatably couples the turbine output shaft 304 to the HPC shaft 224, and a disengaged position that discouples the turbine output shaft 304 from the HPC shaft 224. In the disengaged position, the clutch 318 prevents power (e.g., horsepower) from being transmitted from the PR turbine 250 to the HPC shaft 224. In this way, the clutch 318 can be used to deactivate the PR turbine 250 when power recovery is not required (e.g., during taxiing). The power recovery system 202 is external to the engine core 204 of the aircraft engine 110. For example, the PR turbine 250, gearbox 306, and / or clutch 318 are located within the engine nacelle 208 (e.g., upper bifurcation) of the aircraft engine 110. Furthermore, although the second gear 266 is shown operatively coupled to the HPC shaft 224 in the illustrated example, in other examples, the second gear 266 may be operatively coupled to and driven by the LPC shaft 222 of the LPC 218 or any other drive shaft of the aircraft engine 110. In some examples, the transmission 260 (e.g., gearbox 306, turbine output shaft 304) may be operatively coupled to one or more other systems used in the aircraft 100, such as generators and / or hydraulic pumps (e.g., instead of HPC shaft 224). Gearbox 306 is a multi-speed gearbox that can be disengaged via clutch 318, allowing a wide range of operating conditions and / or allowing the bleed air system 200 to handle failure mode scenarios of the PR turbine 250.

[0040] The PR turbine 250 illustrated is a radial-inflow turbine. To account for varying inflow conditions (e.g., bleed air pressure fluctuations) and / or varying outflow demands, the PR turbine 250 includes adjustable nozzles or variable inlet guide vanes 320. The variable inlet guide vanes 320 enable the PR turbine 250 to handle a variable range of inlet conditions and outflow demands. More specifically, in some examples, the variable inlet guide vanes 320 can be adjusted to achieve higher or lower airflow rates, temperatures, and / or pressures at turbine outlet 254. Thus, the turbine discharge pressure at turbine outlet 254 is regulated by adjusting the variable inlet guide vanes 320. In other examples, the PR turbine 250 may include movable blades, diffuser guide vanes, bladeless diffusers, or systems with port shrouds, which may be employed to account for varying inflow conditions and outflow demands, and / or any other variable geometry to handle a range of variations in inlet conditions and outflow demands.

[0041] Figure 4 yes Figure 3 The illustrated example clutch 318 is a front view. The clutch 318 shown is a wedge clutch. Clutch 318 is a one-way mechanical clutch. Clutch 318 includes an outer race 402, an inner race 404, and a wedge 406 (e.g., a spring-loaded wedge) circumferentially positioned between the inner race 404 and the outer race 402. The wedge 406 is operatively engaged and operatively disengaged from the inner race 404 and the outer race 402 by friction. For example, a gearbox output shaft 316 is coupled to the outer race 402, and a drive shaft 262 is coupled (e.g., fixed or keyed) to the inner race 404. Specifically, when the gearbox output shaft 316 rotates (e.g., in the first direction), the outer race 402 drives the inner race 404 via frictional engagement of the wedge 406, and when the gearbox output shaft 316 does not rotate, the inner race 404 can rotate freely (e.g., the outer race 402 does not drive the inner race 404). Although in Figure 4 A wedge clutch is shown, but the transmission 260 can employ any other suitable clutch configured to engage and disengage the turbine output shaft 304 and the HPC shaft 224. In some examples, the transmission 260 can employ an electronic clutch. In some examples, the transmission 260 can employ a planetary gear system (e.g., a power-split planetary gear system), a multi-speed discrete ratio system, a fixed ratio system, and / or any other suitable transmission. In some examples, the transmission 260 may include a fixed-ratio gear train disposed between the turbine output shaft 304 and the drive shaft 262.

[0042] Figure 5 yes Figures 1 to 4The diagram shows a bleed air system 200. To provide bleed air to aircraft systems (e.g., ECS 236, TAI 238, etc.), the bleed air system 200 employs a bleed air system controller 500. The bleed air system 200 includes a first TAI channel 502 and a second TAI channel 504. The first TAI channel 502 is used for fluid coupling of a first bleed air port 242 to TAI 238, and the second TAI channel 504 is used for fluid coupling of a second bleed air port 244 to TAI 238. In some examples, TAI 238 receives bleed air from the first bleed air port 242 via the first TAI channel 502, bleed air from the second bleed air port 244 via the second TAI channel 504, and / or a mixture of bleed air from the first bleed air port 242 and the second bleed air port 244 via the first TAI channel 502 and the second TAI channel 504.

[0043] The power recovery system 202 includes a low-pressure power recovery (LPPR) passage 506 and a high-pressure power recovery (HPPR) passage 508. The LPPR passage 506 fluidly couples a first bleed port 242 to a turbine inlet 252, and the HPPR passage 508 fluidly couples a second bleed port 244 to a turbine inlet 252. For example, LPPR 506 and HPPR 508 are fluidly coupled at a junction 507, and a PR passage 509 fluidly couples LPPR 506 and HPPR 508 to a turbine inlet 252. A power recovery (PR) manifold 510 fluidly couples a turbine outlet 254 to a precooler 256. As used herein, passages or manifolds include one or more pipes, conduits, hoses, and / or other fluid flow systems or devices.

[0044] To provide bleed air to the precooler 256 when the power recovery system 202 is in a deactivated state, the bleed air system 200 includes a main manifold 512. The main manifold 512 is fluidly coupled to a first bleed air port 242 and / or a second bleed air port 244. In the illustrated example, the main manifold 512 is fluidly coupled to the first bleed air port 242 via an LPPR channel 506 and to the second bleed air port 244 via an HPPR channel 508. In some examples, the main manifold 512 is fluidly coupled to the first bleed air port 242 and / or the second bleed air port 244 via corresponding dedicated (e.g., isolated) channels. The main manifold 512 is fluidly coupled to the precooler 256. In the illustrated example, the main manifold 512 is fluidly coupled to a PR manifold 510 upstream of the precooler 256. In some examples, the bleed air from the main manifold 512 may be mixed with the bleed air in the PR manifold 510 before the mixed bleed air is provided to the precooler 256.

[0045] The precooler 256 includes a precooler inlet 514 and a precooler outlet 516. The precooler inlet 514 receives bleed air from the PR manifold 510 and / or the main manifold 512. The precooler outlet 516 is fluidly coupled to the ECS 236 via the ECS passage 518 and to other systems 240 via the auxiliary passage 520. To cool the bleed air flowing through the precooler 256, the bleed air is directed through a heat exchanger section 522 of the precooler 256. The precooler 256 of the illustrated example includes a heat exchanger section 522 between the precooler inlet 514 and the precooler outlet 516. The heat exchanger section 522 receives bleed air from the PR manifold 510 and / or the main manifold 512. Cooling fluid (e.g., fan air 210a) flows through the precooler 256 between a cooling fluid inlet 524 and a cooling fluid outlet 526 to remove heat and thus cool the bleed air flowing through the heat exchanger section 522. The bleed air flowing through heat exchanger section 522 is fluidly isolated from the cooling fluid (i.e., the bleed air is not mixed with fan air 210a). In order to provide cooling fluid to precooler 256, bleed air system 200 includes fan duct 290 to guide fan air 210a from fan 206 to cooling fluid inlet 524.

[0046] The precooler 256 illustrated includes a precooler bypass 528 to allow bleed air to bypass the precooler 256 (e.g., heat exchanger section 522). When flowing through the precooler bypass 528, the bleed air is not cooled. To direct the bleed air flow between the heat exchanger section 522 and the precooler bypass 528, the precooler 256 includes a precooler valve 530 and an actuator 532 (e.g., a linear actuator). The actuator 532 moves the precooler valve 530 to a first position to allow bleed air to flow through the heat exchanger section 522 and to block or limit bleed air flow through the precooler bypass 528, and to a second position to allow bleed air to flow through the precooler bypass 528 and to block or limit bleed air flow through the heat exchanger section 522. An exemplary heat exchanger that can implement the precooler 256 is described in U.S. Patent Application 13 / 624,612, filed September 21, 2012, which is incorporated herein by reference. In some examples, the precooler 256 may be a heat exchanger without a precooler bypass 528.

[0047] To start the aircraft engine 110, the aircraft engine 110 includes a starter 567. The starter 567 is fluidly coupled to the aircraft engine 110. A starter passage 569 fluidly couples the starter 567 to the precooler inlet 514 of the precooler 256. To start the aircraft engine 110, an auxiliary unit supplies pressurized fluid (pneumatic air) to the starter passage 569 via the precooler outlet 516, through the precooler bypass 528, and the precooler inlet 514. A starter valve 571 moves to the open position to allow fluid in the starter passage 569 to flow to the aircraft engine 110. After the aircraft engine 110 has started, the starter valve 571 moves to the closed position to prevent fluid from flowing through the starter passage 569 to the starter 567.

[0048] During operation, the bleed air system 200 supplies regulated air (e.g., via ECS 236) to the cabin 108 of the aircraft 100 based on the number of passengers in the cabin 108. To determine the mass flow rate of the supply air to be supplied to the cabin 108, the bleed air system controller 500 acquires, retrieves, and / or receives passenger count information from, for example, a database 586 and / or an engine control system 588. Passenger count information may be manually stored in the database 586. For example, in some aircraft, the target flow rate may be 0.55 lb. / min / passenger. The bleed air system controller 500 determines the amount of pressure difference between the ECS 236 and the bleed air system 200 required to provide the target flow rate. The bleed air system controller 500 determines which bleed air port (e.g., first bleed air port 242 or second bleed air port 244) is generating sufficient pressurized bleed air to meet the target flow rate. Furthermore, the power recovery system 202 determines, via the bleed air system controller 500, whether the pressurized bleed air is sufficient to provide the target flow rate to the ECS 236. When the pressure is insufficient, the bleed air system controller 500 deactivates the power recovery system 202. When the pressure is sufficient, the bleed air system controller 500 activates the power recovery system 202.

[0049] The bleed air system controller 500 enables the bleed air system 200 to extract bleed air from a first bleed air port 242 (e.g., during a high-power setting) and from a second bleed air port 244 (e.g., during a low-power setting). For example, a high-power setting can occur when the aircraft engine 110 generates thrust exceeding a thrust threshold (e.g., during takeoff, climb, cruise, descent, etc.), while a low-power setting can occur when the aircraft engine 110 generates thrust not exceeding a thrust threshold (e.g., during taxiing, flight taxiing, etc.). For example, during high-power setting operation, the parameters (e.g., pressure or temperature) of the bleed air at the first bleed air port 242 are greater than those during low-power setting operation. Therefore, during low-power setting conditions, the bleed air system 200 extracts bleed air from the second bleed air port 244 because the bleed air at the first bleed air port 242 may be insufficient to provide the target flow rate, temperature, and / or pressure bleed air to the ECS 236. During high-power setup conditions, the bleed air system 200 draws bleed air from the first bleed air port 242 because the bleed air at the first bleed air port 242 is sufficient to provide the target flow rate, temperature, and / or pressure to the ECS 236. Performance efficiency increases when bleed air is drawn from the first bleed air port 242 because the engine compressor 216 compresses fan air 210b fewer times at the first bleed air port 242 (e.g., the fourth compression stage) than at the second bleed air port 244 (e.g., the tenth compression stage). Therefore, in this example, drawing bleed air from the first bleed air port 242 is more desirable than drawing bleed air from the second bleed air port 244.

[0050] To control the bleed air flow within and / or to the power recovery system 202, the bleed air system 200 includes one or more control valves 534-550. For example, to control the flow of bleed air from the first bleed air port 242 to the TAI 238 and turbine inlet 252 via the LPPR passage 506, the bleed air system 200 includes a first control valve 534 (e.g., an intermediate pressure check valve (IPCV)). A second control valve 536 (e.g., a high-pressure shut-off valve (HPSOV)) controls the flow of bleed air from the second bleed air port 244 to the turbine inlet 252 via the HPPR passage 508. In the example shown, the second control valve 536 includes a sensing line 536a to measure the pressure of the fluid downstream of the second control valve 536. In this way, the second control valve 536 can regulate the pressure of the bleed air downstream of the second control valve 536 (e.g., at the outlet of the second control valve 536) based on a desired preset pressure value (e.g., a setpoint). The preset pressure value can be set mechanically and / or provided by the bleed air system controller 500 via a signal (e.g., an analog signal). To control the flow of bleed air from the LPPR channel 506 and / or HPPR channel 508 to the turbine inlet 252, the power recovery system 202 includes a third control valve 538 (e.g., a shut-off valve (SOV)). The third control valve 538 provides a bleed air control valve to control the flow of bleed air to the turbine inlet 252.

[0051] To bypass the PR turbine 250 and control the flow of bleed air via the main manifold 512 to the precooler 256, the bleed air system 200 includes a fourth control valve 540 (e.g., a pressure regulating shut-off valve (PRSOV)). For example, when the PR turbine 250 is not needed or is not desired, the fourth control valve 540 allows bleed air to bypass the PR turbine 250. For example, if the pressure of the bleed air from the first bleed air port 242 is insufficient to meet the pressure requirements of the ECS 236, the bleed air can bypass the PR turbine 250, thus preventing a pressure drop across the PR turbine 250. In the example shown, the fourth control valve 540 includes a sensing line 540a to sense the fluid pressure in the main manifold 512 downstream of the fourth control valve 540. In this way, the fourth control valve 540 can regulate the pressure downstream of the fourth control valve 540 (e.g., at the outlet of the fourth control valve 540) based on a desired preset value (e.g., a setpoint). The preset values ​​can be set mechanically and / or provided by the bleed air system controller 500 via a signal (e.g., an analog signal).

[0052] The bleed air system 200 includes a fifth control valve 542 (e.g., a low-level anti-icing valve) to control the bleed airflow to TAI 238, a sixth control valve 546 to control the bleed airflow to ECS 236, and a seventh control valve 548 to control the bleed airflow to other systems 240. To control the flow of cooling fluid between the cooling fluid inlet 524 and cooling fluid outlet 526 of the precooler 256, the bleed air system 200 includes a fan valve 550.

[0053] Each of the control valves 534-550 operates independently of the other valves and can operate between an open position (e.g., a fully open position or state) that allows fluid flow through the corresponding control valve 534-550 and a closed position (e.g., a fully closed position or state) that prevents or restricts fluid flow through the corresponding control valve 534-550. The control valves 534-550 may include pressure regulating valves (PRVs), pressure regulating shut-off valves (PRSOVs), shut-off valves (SOVs), high-pressure shut-off valves (HPSOVs), intermediate pressure check valves (IPCVs), anti-backflow valves, multi-flow directional valves, three-way valves, four-way valves, etc., and / or any other air control device. In some examples, the bleed air system 200 may include more or fewer control valves 534-550, channels 502-508, 518, 520, and / or manifolds 510-512 than disclosed herein. For example, although control valves 534-550, channels 502-508, 518, 520 and / or manifolds 510-512 are in Figure 5 As shown in the diagram. One or more additional valves, passages, and / or manifolds may be incorporated into the bleed air system 200.

[0054] To measure the parameters or characteristics of the bleed air, the bleed air system 200 includes one or more sensors 552-566 (e.g., temperature sensors, pressure sensors, flow sensors, humidity sensors, etc.). For example, the bleed air system 200 includes one or more sensors 552-566 to measure the temperature, pressure, flow rate, and / or any other parameters or characteristics of the bleed air system 200. For example, one or more sensors 552 are coupled to LPPR channel 506 to measure the pressure and / or flow rate of the bleed air flowing to turbine inlet 252 via LPPR channel 506 and / or HPPR channel 508. One or more sensors 554 are coupled near turbine inlet 252 to measure the temperature of the bleed air at turbine inlet 252. One or more sensors 556 are coupled to PR manifold 510 to measure the pressure of the bleed air leaving turbine outlet 254 before the bleed air flows to precooler 256. One or more sensors 558 are coupled to PR manifold 510 to measure the temperature of the bleed air leaving turbine outlet 254. One or more sensors 560 are coupled near the precooler inlet 514 (downstream of the main manifold 512) to measure the pressure of the bleed air entering the precooler inlet 514. One or more sensors 562 are coupled near the precooler inlet 514 (downstream of the main manifold 512) to measure the temperature of the bleed air entering the precooler inlet 514. One or more sensors 564 are coupled near the precooler outlet 516 (downstream of the precooler outlet 516) to measure the pressure of the bleed air leaving the precooler outlet 516. One or more sensors 566 are coupled near the precooler outlet 516 (downstream of the precooler outlet 516) to measure the temperature of the bleed air leaving the precooler outlet 516. Additional sensors may be provided at various other locations to similarly measure one or more parameters of the supply air at various points in the bleed air system 200.

[0055] To control the operation of the power recovery system 202, the bleed air system 200 includes a bleed air system controller 500. The bleed air system controller 500 can be implemented by a controller or a processor, such as in conjunction with... Figure 15 The publicly disclosed processor platform 1500 has a processor 1512. The bleed air system controller 500 is communicatively coupled to one or more control valves 538-550, one or more sensors 552-566, and the variable inlet guide vanes 320 of the PR turbine 250. Figure 3 ( ), gearbox 306, clutch 318, actuator 532 and / or various means for controlling bleed air system 200 and / or power recovery system 202 and / or any other means for monitoring various parameters (e.g., mass flow rate, pressure, temperature, etc.).

[0056] In the example shown, the bleed air system controller 500 includes a bleed air regulator 570, a power recovery determiner 572, a power recovery operator 574, a valve operator 576, a precooler operator 578, an input / output (I / O) module 580, and a comparator 582 communicatively coupled via a bus 584. In the example shown, the bleed air system controller 500 is communicatively coupled to an engine control system 588, which receives or determines operating parameters and / or flight conditions, including, for example, altitude, air velocity, throttle position, air pressure, air temperature, humidity, engine speed, air density, passenger capacity, engine speed (RPM), HP-axis RPM, LP-axis RPM, high power setting conditions, low power setting conditions, and / or other parameters. The database 586, communicatively coupled to the bleed air system controller 500, includes PR turbine mapping data and thresholds (e.g., bleed air pressure threshold, turbine outlet temperature and / or pressure threshold, precooler inlet temperature and / or pressure threshold, turbine inlet temperature and / or pressure threshold, HP shaft RMP threshold or range, precooler outlet temperature and / or pressure threshold, etc.).

[0057] I / O module 580 receives signals from one or more sensors 552-566, which measure one or more parameters of the bleed air system 200. Comparator 582 can be used to compare the measured values ​​of the parameters provided by one or more sensors 552-566 with one or more thresholds or threshold ranges (e.g., stored in a database 586 accessible by the bleed air system controller 500). Based on whether the parameters meet the thresholds or threshold ranges, valve actuator 576 can operate one or more valves 534-548 to provide bleed air with desired parameters (e.g., pressure and / or temperature) to ECS 236, TAI 238, and / or other systems 240. Furthermore, valve actuator 576 can operate fan valve 550 to control the flow of cooling fluid through precooler 256. For example, valve actuator 576 controls the operating state of valves 536-550. For example, any of valves 536-550 can operate between an open state (e.g., fully open position) and a closed state (e.g., fully closed position) and in any state or position in between (e.g., half open position) to control fluid flow through the corresponding TAI channels 502 and 504, LPPR channel 506, HPPR channel 508, main manifold 512, ECS channel 518, auxiliary channel 520, PR turbine 250, etc.

[0058] In the example shown, the first control valve 534 is a check valve. Therefore, the valve operator 576 does not control the operation of the first control valve 534. For example, the first control valve 534 is a one-way spring-loaded check valve that operates based on the pressure differential across the check valve. If the pressure downstream of the first control valve 534 is less than the bleed pressure at the first bleed port 242, the first control valve 534 moves to the open position to allow bleed air from the first bleed port 242 to flow into the LPPR passage 506. If the pressure downstream of the first control valve 534 is greater than the bleed pressure at the first bleed port 242 (e.g., when the second bleed port 244 is open), the first control valve 534 moves to the closed position to prevent bleed air from the first bleed port 242 from flowing into the LPPR passage 506. However, in some examples, the first control valve 534 may be a shut-off valve controlled by the valve operator 576 in an open position, a closed position, and / or in one or more intermediate positions between the open and closed positions.

[0059] During operation, the bleed air regulator 570 determines whether the pressure of the bleed air flowing through the first control valve 534 from the first bleed air port 242 is sufficient to provide the target flow rate and / or pressure to the ECS 236. For example, the bleed air regulator 570 receives one or more parameters via the I / O module 580 from the engine control system 588 and / or one or more sensors 552-566 to determine whether bleed air is available at the first bleed air port 242 based on the temperature and / or pressure of the bleed air at the first bleed air port 242 or the temperature and / or pressure of the bleed air at the second bleed air port 244. In some examples, the bleed air regulator 570 determines whether the aircraft engine 110 is in a high-power setting (e.g., based on altitude (e.g., cruise), angle of attack, or thrust (e.g., takeoff, climb, descent, or landing)) or a low-power setting (e.g., based on altitude, thrust, taxiing, flight idling, etc.).

[0060] In the example shown, sensor 552 (e.g., an intermediate pressure sensor) measures the pressure of the bleed air in LPPR channel 506 and signals it to bleed air system controller 500. Bleed air regulator 570 determines via comparator 582 whether the pressure is greater than a pressure threshold (e.g., 40 psi) retrieved from database 586 and / or engine control system 588. If the measured pressure is greater than the pressure threshold, bleed air regulator 570 commands second control valve 536 (e.g., via valve operator 576) to move to the closed position. When second control valve 536 is closed, the pressure difference across first control valve 534 causes first control valve 534 to move to the open position to allow bleed air to flow from first bleed air port 242 to LPPR channel 506. If the pressure measured by sensor 552 is greater than the pressure threshold, bleed air regulator 570 commands second control valve 536 (e.g., via valve operator 576) to move to the open position. When the second control valve 536 is opened, the pressure difference across the first control valve 534 causes the first control valve 534 to move to the closed position to prevent bleed air from flowing from the first bleed port 242 to the LPPR channel 506.

[0061] The power recovery determiner 572 obtains, collects, and / or otherwise receives flight condition and / or aircraft engine operating condition information from the bleed air regulator 570 and / or engine control system 588. For example, the power recovery determiner 572 receives pressure and / or temperature values ​​and / or target bleed air flow rates, target pressures, and / or target temperatures from one or more sensors 552-566 via I / O module 580 for use by ECS 236, other systems 240, etc. Furthermore, the power recovery determiner 572 receives, retrieves, and / or otherwise obtains PR turbine performance mapping information from database 586 and / or receives, retrieves, and / or otherwise obtains the speed (e.g., RPM) of HPC shaft 224.

[0062] Based on received, retrieved, and / or otherwise obtained parameter and / or conditional information (e.g., bleed air pressure, bleed air temperature, target flow rate, turbine mapping, HP shaft RPM, etc.), the power recovery determiner 572 determines whether the PR turbine 250 is capable of extracting energy from the bleed air and adding power (e.g., 575 horsepower) to the HPC shaft 224. For example, when bleed air flows through the PR turbine 250, the PR turbine 250 reduces the bleed air pressure and / or temperature. If the pressure, temperature, and / or flow rate obtained at the turbine outlet 254 are insufficient to meet the needs of the ECS 236 or other systems 240, the power recovery determiner 572 may determine to deactivate the power recovery system 202.

[0063] For example, the power recovery determiner 572 determines whether one or more parameters of the bleed air system 200 (e.g., target pressure, target temperature, target flow rate, HP shaft RPM, etc.) can be achieved based on one or more parameters of the bleed air at turbine inlet 252 and the resulting one or more parameters of the bleed air at turbine outlet 254. For example, after processing the bleed air via PR turbine 250 to extract energy, the power recovery determiner 572 determines whether one or more parameters of the bleed air extracted from the first bleed air port 242 or the second bleed air port 244 are sufficient to achieve the target temperature, target pressure, target flow rate, etc. of the bleed air at turbine outlet 254 (e.g., for precooler inlet 514 and / or precooler outlet 516). For example, after recovering energy from the bleed air by processing the bleed air passing through PR turbine 250, the power recovery determiner 572 determines whether the pressure of the bleed air at turbine inlet 252 is sufficient to provide the target pressure at turbine outlet 254. In some examples, the power recovery determiner 572 determines whether the temperature of the bleed air at turbine inlet 252 is sufficient to provide the target temperature at turbine outlet 254. In some examples, the power recovery determiner 572 determines whether the temperature of the bleed air at turbine inlet 252 is sufficient to provide the target temperature at precooler inlet 514 by mixing the bleed air at turbine outlet 254 (e.g., possibly below the target temperature at precooler 256) with the bleed air from main manifold 512 before the bleed air flows to precooler inlet 514. In some examples, the power recovery determiner 572 determines whether to activate PR turbine 250 based on the speed (e.g., RPM) of HPC shaft 224 and / or the speed (e.g., RPM) of drive shaft 262. If the power recovery determiner 572 determines that the operating parameters of the bleed air are sufficient to activate power recovery system 202, the power recovery determiner 572 commands valve operator 576 to operate one or more valves 536-550. When the regenerative braking system is activated, the regenerative braking actuator 574 compares the speed (e.g., RPM) of the HPC shaft 224 with the speed (e.g., RPM) of the drive shaft 262. Based on the fixed gear ratio between the first gear 264 and the second gear 266, the regenerative braking actuator 574 controls the gearbox 306 so that the drive shaft 262 can operate at a speed that matches the speed of the HPC shaft 224 based on the fixed ratio of the first gear 264 to the second gear 266.

[0064] Furthermore, when the power recovery system 202 is activated, valve actuator 576 commands or otherwise moves the third control valve 538 to the open position, and power recovery determiner 572 commands power recovery actuator 574 to operate the PR turbine 250. For example, power recovery actuator 574 operates or adjusts the variable inlet guide vanes 320 of turbine inlet 252. Figure 3 (e.g., turbine nozzle), to make clutch 318 ( Figure 3 The clutch 318 engages and enables the PR turbine 250 to transmit horsepower 575 to the HPC shaft 224 via the transmission 260. After the clutch 318 is engaged, the power recovery operator 574 commands or otherwise adjusts the variable inlet guide vanes 320 (e.g., increases or decreases the angle position) to affect the mass flow rate (based on the pressure difference of the bleed air flowing between the turbine inlet 252 and the turbine outlet 254 required to achieve the target flow rate, target pressure, target temperature used by the ECS 236 or other system 240), the target speed (e.g., RPM) of the drive shaft 262 based on the speed (e.g., RPM) of the HPC shaft 224 and / or the gear ratio, etc.

[0065] If the power recovery determiner 572 determines that the power recovery system 202 should be deactivated, the bleed air regulator 570 commands or otherwise causes the valve operator 576 to control the third control valve 538 to the closed position and the fourth control valve 540 to the open position, so that bleed air flows through the main manifold 512 to the precooler inlet 514.

[0066] Regardless of whether the power recovery system 202 is activated or deactivated, the precooler operator 578 determines whether the temperature of the bleed air at the precooler outlet 516 is greater than a predetermined maximum threshold and / or within a predetermined threshold range. The precooler operator 578 controls the precooler valve 530 via actuator 532 and fan valve 550 to cool the bleed air via precooler 256, or controls the precooler valve 530 via actuator 532 to allow the bleed air to flow through the precooler bypass 528 without cooling.

[0067] Despite Figure 5 An exemplary manner of implementing the bleed air system controller 500 is shown in the figure. Figure 5 One or more of the elements, processes, and / or devices shown may be combined, divided, rearranged, omitted, eliminated, and / or implemented in any other way. Furthermore, the bleed air regulator 570, power recovery determiner 572, valve operator 576, precooler operator 578, input / output (I / O) module 580, comparator 582, and / or, more generally, Figure 5 The exemplary bleed air system controller 500 shown can be implemented using hardware, software, firmware, and / or any combination of hardware, software, and / or firmware. Thus, for example, a bleed air regulator 570, a power recovery determiner 572, a valve operator 576, a precooler operator 578, an input / output (I / O) module 580, a comparator 582, and / or, more generally, Figure 5Any of the exemplary bleed air system controllers 500 shown can be implemented by one or more analog or digital circuits, logic circuits, programmable processors, programmable controllers, graphics processing units (GPUs), digital signal processors (DSPs), application-specific integrated circuits (ASICs), programmable logic devices (PLDs), and / or field-programmable logic devices (FPLDs). When interpreting any of the device or system solutions of this patent to cover purely software and / or firmware implementations, at least one of the following—bleed air regulator 570, power recovery determiner 572, valve operator 576, precooler operator 578, input / output (I / O) module 580, and comparator 582—is hereby explicitly defined as including non-transitory computer-readable storage devices or storage disks such as memory, digital versatile disks (DVDs), optical discs (CDs), Blu-ray discs, etc., including software and / or firmware. Furthermore, Figure 5 The exemplary bleed air system controller 500 shown may include, except for, or replace Figure 5 One or more elements, processes, and / or devices other than those shown, and / or may include more than one or all of any of the elements, processes, and devices shown. As used herein, the phrase “in communication,” including its variants, covers direct and / or indirect communication via one or more intermediate components, and does not require direct physical (e.g., wired) communication and / or continuous communication, but additionally includes selective communication at periodic intervals, scheduled intervals, non-periodic intervals, and / or one-off events.

[0068] Figure 6 It is in the first operating mode 600 Figures 1 to 5 A schematic diagram of the bleed air system 200 is shown. In the first operating mode 600, the aircraft engine 110 is in a low power setting 602, and the ambient air temperature is below an ambient temperature threshold (e.g., 75 degrees Fahrenheit). For example, in the first operating mode 600, the aircraft 100 is in taxi mode, idle mode, and / or flight idle mode. In the first operating mode 600, the power recovery system 202 is in a deactivated state 604, and power (e.g., 575 horsepower) is not generated by the PR turbine 250.

[0069] In the first operating mode 600, bleed air flows from the second bleed port 244 through the HPPR passage 508 and the main manifold 512, and flows to the precooler inlet 514. For example, the bleed air system controller 500 moves the second control valve 536 and the fourth control valve 540 to the open position to supply bleed air from the second bleed port 244 to the precooler inlet 514 via the HPPR passage 508 and the main manifold 512. The first control valve 534 restricts or prevents bleed air from entering the LPPR passage 506 from the first bleed port 242, and the third control valve 538 is in the closed position to prevent bleed air from flowing towards the PR turbine 250. The bleed air flows to the ECS 236 through the precooler bypass 528.

[0070] For example, in the first operating mode 600, the bleed air regulator 570 determines that the aircraft 100 is in a low power setting 602 based on information received, retrieved, and / or otherwise obtained from the engine control system 588. Furthermore, the power recovery determiner 572 receives, retrieves, or otherwise obtains a measured pressure of the bleed air in the LPPR channel 506 via sensor 552 and compares the measured pressure with a pressure threshold obtained from a database 586 (e.g., via comparator 582). In some examples, the bleed air regulator 570 determines that the aircraft engine 110 is in a low power setting 602 by comparing the speed (e.g., RPM) of the HPC shaft 224 with a low power setting RPM threshold (e.g., an RPM range or a table stored in the database 586). Because the aircraft engine 110 is in a low power setting 602, the power recovery determiner 572 determines that the measured pressure does not exceed a pressure threshold (e.g., 40 psi). In response to determining that the aircraft engine 110 is in a low power setting 602, the bleed air regulator 570 commands the valve operator 576 to open the second control valve 536 and the fourth control valve 540 to allow bleed air from the second bleed air port 244 to flow through the HPPR passage 508 and the main manifold 512 to the precooler 256.

[0071] Furthermore, the power recovery determiner 572 determines to move the power recovery system 202 to a deactivated state 604. To deactivate the power recovery system 202, the power recovery determiner 572 commands the valve operator 576 to move the third control valve 538 to the closed position to prevent bleed air from flowing through the PR turbine 250. Additionally, the precooler operator 578 receives, retrieves, and / or otherwise obtains a measured temperature of the bleed air at the precooler inlet 514 via sensor 562, and obtains a target temperature of the ECS 236 via database 586. The precooler operator 578 compares the measured temperature with the target temperature. In this example, the precooler operator 578 determines that the measured temperature does not exceed the target temperature and commands or otherwise causes the actuator 532 to move the precooler valve 530 to a second position to allow bleed air to flow through their precooler bypass 528.

[0072] Figure 7 It is in the second operating mode 700 Figures 1 to 5 A schematic diagram of the bleed air system 200 is shown. In the second operating mode 700, the aircraft engine 110 operates in a low-power setting 602, and the ambient air temperature is above an ambient temperature threshold (e.g., 75 degrees Fahrenheit). Figure 6 Conversely, the bleed air is cooled via precooler 256 (e.g., to lower the temperature of the bleed air). For example, precooler operator 578 determines that the measured temperature from sensor 562 at precooler inlet 514 exceeds the target temperature at precooler outlet 516. To activate precooler 256, precooler operator 578 commands or otherwise causes actuator 532 to move precooler valve 530 to a first position to allow bleed air to flow through heat exchanger section 522. Furthermore, precooler operator 578 commands or otherwise causes valve operator 576 to open fan valve 550 to allow fan air 210a ( Figure 2 Cooling fluid flows from cooling fluid inlet 524 to cooling fluid outlet 526 to cool the bleed air flowing through heat exchanger section 522. Precooler operator 578 receives a second measured temperature from sensor 566 downstream of precooler outlet 516 and compares the second measured temperature with a target temperature. Precooler operator 578 or valve operator 576 regulates (e.g., opens and / or closes) fan valve 550 to adjust the second measured temperature downstream of precooler outlet 516 to the target temperature.

[0073] Figure 8 In the third operating mode 800 Figures 1 to 5 A schematic diagram of the bleed air system 200 is shown. In the third operating mode 800, the aircraft engine 110 is in a high-power setting 802, and the ambient air temperature is below an ambient temperature threshold (e.g., 75 degrees Fahrenheit). For example, the third operating mode 800 can occur during takeoff, cruise, and / or landing. In the third operating mode 800, the power recovery system 202 is activated 804, and the PR turbine 250 extracts power (e.g., 575 horsepower) from the bleed air.

[0074] In the third operating mode 800, bleed air flows from the first bleed air port 242 to the PR turbine 250. As the bleed air flows between the turbine inlet 252 and the turbine outlet 254, the PR turbine 250 expands the bleed air. During this expansion, the pressure and / or temperature of the bleed air decreases as it flows through the PR turbine 250. The PR turbine 250 converts energy into power and transmits the converted energy to the HPC shaft 224 via the transmission 260. The bleed air at the turbine outlet 254 flows to the precooler 256 via the PR manifold 510.

[0075] To supply bleed air from the first bleed port 242 to the turbine inlet 252 via the LPPR passage 506, the bleed air system controller 500 moves the second control valve 536 and the fourth control valve 540 to the closed position to prevent bleed air from flowing from the second bleed port 244 to the turbine inlet 252 via the HPPR passage 508 or from flowing through the main manifold 512. The first control valve 534 moves to the open position to allow bleed air from the first bleed port 242 to flow to the PR turbine 250 based on the pressure difference across the first control valve 534. The bleed air flows to the ECS 236 via the precooler bypass 528.

[0076] In the third operating mode 800, the bleed air regulator 570 determines that the aircraft 100 is in a high-power setting 802 based on information received, retrieved, and / or otherwise obtained from the engine control system 588. For example, the bleed air regulator 570 determines that the aircraft engine 110 is in a high-power setting mode by comparing the speed (e.g., RPM) of the HPC shaft 224 with a high-power setting RPM threshold (e.g., an RPM range or table stored in a database 586). In some examples, the engine control system 588 receives the pressure value of the bleed air in the engine compressor 216 and determines a selection between a first bleed air port 242 and a second bleed air port 244 based on the measured pressure value. In response to determining that the aircraft engine 110 is in a high-power setting 802, the bleed air regulator 570 commands the valve operator 576 to close the second control valve 536 (reducing the pressure in the LPPR channel 506) so that the first control valve 534 can open and allow bleed air from the first bleed air port 242 to flow into the LPPR channel 506.

[0077] In some examples, the power recovery determiner 572 receives, retrieves, or otherwise obtains a measured pressure of the bleed air in the LPPR channel 506 via sensor 552, and compares the measured pressure with a pressure threshold, target pressure, etc., obtained from a database 586 (e.g., via comparator 582). When the aircraft engine 110 is operating in a high power setting 802, the power recovery determiner 572 determines that the measured pressure exceeds a pressure threshold (e.g., 40 psi) and therefore determines to activate the power recovery system 202. To activate the power recovery system 202, the power recovery determiner 572 commands valve operator 576 to open the third control valve 538.

[0078] The power recovery actuator 574 measures the bleed air pressure at turbine inlet 252 and turbine outlet 254, and adjusts the variable inlet guide vanes 320 of the PR turbine 250 to adjust (e.g., increase or decrease) the output power to the HPC shaft 224. Furthermore, the power recovery determiner 572 and / or the power recovery actuator 574 receive bleed air pressure and / or temperature values ​​from sensors 560, 562 at the precooler inlet 514. If the pressure and / or temperature at the precooler inlet 514 exceeds a precooler inlet pressure threshold and / or precooler inlet temperature threshold (e.g., retrieved from database 586), the valve actuator 576 moves the fourth control valve 540 to the closed position to prevent bleed airflow through the main manifold 512. If the pressure and / or temperature at the precooler inlet 514 does not exceed the precooler inlet pressure threshold and / or precooler inlet temperature threshold (e.g., retrieved from database 586), then valve operator 576 moves the fourth control valve 540 to the open position to allow all bleed air to flow through the main manifold 512.

[0079] In addition, the precooler operator 578 receives, retrieves, and / or otherwise obtains a measured temperature of the bleed air at the precooler outlet 516 via sensor 566, and a target temperature of the ECS 236 via database 586. The precooler operator 578 compares the measured temperature with the target temperature. In this example, the precooler operator 578 determines that the measured temperature does not exceed the target temperature and commands or otherwise causes the actuator 532 to move the precooler valve 530 to a second position to allow bleed air to flow through the precooler bypass 528.

[0080] Figure 9 It is in the fourth operating mode 900 Figures 1 to 5 A schematic diagram of the bleed air system 200 is shown. In the fourth operating mode 900, the aircraft engine 110 operates in a high-power setting 802, and the ambient air temperature is above an ambient temperature threshold (e.g., 75 degrees Fahrenheit). The fourth operating mode 900 is substantially similar to the third operating mode 800, except that the bleed air is cooled via precooler 256 (e.g., to reduce the temperature of the bleed air). For example, precooler operator 578 determines that the measured temperature at precooler outlet 516 from sensor 566 exceeds a target temperature. To activate precooler 256, precooler operator 578 commands or otherwise causes actuator 532 to move precooler valve 530 to a first position to allow bleed air to flow through heat exchanger section 522. Furthermore, precooler operator 578 commands or otherwise causes valve operator 576 to open fan valve 550 to allow fan air 210a ( Figure 2Cooling fluid flows from cooling fluid inlet 524 to cooling fluid outlet 526 to cool the bleed air flowing through heat exchanger section 522. Precooler operator 578 receives downstream measured temperature from sensor 566 downstream of precooler outlet 516 and compares the downstream measured temperature with a target temperature. Precooler operator 578 or valve operator 576 regulates (e.g., opens and / or closes) fan valve 550 to adjust the downstream measured temperature downstream of precooler outlet 516 to the target temperature.

[0081] Figure 10 It is in the fifth operating mode 1000 Figures 1 to 5 A schematic diagram of the bleed air system 200 is shown. In the fifth operating mode 1000, the aircraft engine 110 operates at a medium power setting 1002 (e.g., between a low power setting and / or a high power setting 802) and the ambient air temperature is below an ambient temperature threshold (e.g., 75 degrees Fahrenheit). The fifth operating mode 1000 is substantially similar to the third operating mode 800, except that the bleed air exiting the turbine outlet 254 is mixed with the bleed air flowing through the main manifold 512. For example, the bleed air supplied by the turbine outlet 254 is mixed with the bleed air supplied by the main manifold 512 to increase the parameters (e.g., pressure or temperature) of the bleed air before it flows to the precooler inlet 514. For example, the power recovery operator 574 determines that the pressure or temperature measured by sensors 560, 562 at the precooler inlet 514 does not exceed the target pressure or temperature at the precooler outlet 516. For example, during medium power setting 1002, the pressure exiting turbine outlet 254 may be too low and / or the temperature of the bleed air exiting turbine outlet 254 may be too cold. In order to activate the bleed airflow through the main manifold 512, valve operator 576 commands or otherwise moves the fourth control valve 540 to the open position to allow fluid to flow through the main manifold 512.

[0082] Figure 11 It is in the sixth operating mode 1100 Figures 1 to 5 A schematic diagram of the bleed air system 200 is shown. In the sixth operating mode 1100, the aircraft engine 110 is in a low power setting 602, and the power recovery system 202 is in an active state 804, and power (e.g., 575 horsepower) is generated by the PR turbine 250. For example, in the sixth operating mode 1100, the power recovery system 202 receives bleed air from the second bleed air port 244. For example, the bleed air flows from the second bleed air port 244 to the turbine inlet 252 via the HPPR channel 508.

[0083] To supply bleed air from the second bleed port 244 to the turbine inlet 252 via the HPPR passage 508, the bleed air system controller 500 moves the second control valve 536 and the third control valve 538 to the open position. The bleed air system controller 500 also moves the first control valve 534 and the fourth control valve 540 to the closed position to prevent bleed air from flowing from the first bleed port 242 to the turbine inlet 252 via the LPPR passage 506 or to prevent bleed air from flowing through the main manifold 512.

[0084] For example, in the sixth operating mode 1100, the bleed air regulator 570 determines that the aircraft 100 is in a low-power setting 602 based on information received, retrieved, and / or otherwise obtained from the engine control system 588. In response to determining that the aircraft engine 110 is in a low-power setting 602, the bleed air regulator 570 commands the valve operator 576 to open the second control valve 536 to allow bleed air flow from the second bleed air port 244 to the HPPR passage 508.

[0085] In addition, the power recovery determiner 572 receives, retrieves, or otherwise obtains measured pressure and / or measured temperature of the bleed air in HPPR channel 508 via sensors 552, 554, and compares the measured pressure with a pressure threshold and / or the measured temperature with a temperature threshold obtained from database 586 (e.g., via comparator 582). If the power recovery determiner 572 determines that the measured pressure exceeds a pressure threshold (e.g., 40 psi) and / or the measured temperature exceeds a temperature threshold, the power recovery determiner 572 determines to activate the power recovery system 202 and commands valve operator 576 to open the third control valve 538.

[0086] The power recovery actuator 574 measures the bleed air pressure at turbine inlet 252 and turbine outlet 254. If the pressure change exceeds a delta pressure threshold retrieved from database 586, the power recovery actuator 574 adjusts the variable inlet guide vanes 320 of the PR turbine 250 to increase power to the HPC shaft 224. Furthermore, the power recovery determiner 572 and / or the power recovery actuator 574 receive bleed air pressure and / or temperature values ​​from sensors 560, 562 at the precooler inlet 514. If the pressure at the precooler inlet 514 exceeds a precooler inlet pressure threshold (e.g., retrieved from database 586), the valve actuator 576 moves the fourth control valve 540 to the closed position to prevent bleed airflow through the main manifold 512. If the pressure at the precooler inlet 514 is less than the precooler inlet pressure threshold (e.g., retrieved from database 586), the valve actuator 576 moves the fourth control valve 540 to the open position to allow bleed airflow through the main manifold 512.

[0087] In addition, the precooler operator 578 receives, retrieves, and / or otherwise obtains the measured temperature of the bleed air at the precooler inlet 514 via sensor 562, and obtains the target temperature of the ECS 236 via database 586. The precooler operator 578 compares the measured temperature with the target temperature. The precooler operator 578 commands or otherwise causes actuator 532 to move the precooler valve 530 to a first position to allow bleed air to flow through the heat exchanger section 522, and causes valve operator 576 to open the fan valve 550 when the measured temperature exceeds the target temperature. The precooler operator 578 commands or otherwise causes actuator 532 to move the precooler valve 530 to a second position to allow bleed air to flow through the precooler bypass 528 when the measured temperature does not exceed the target temperature.

[0088] Figure 12 This is a schematic diagram of an aircraft engine 110 that uses a power recovery system as a starter 1200. For example, Figure 5 The starter 567 of the aircraft engine 110 shown can be omitted or replaced by the power recovery system 202. In some examples, the power recovery system 202 can be... Figure 5 The starter 567 shown provides a starter backup system. To utilize the power recovery system 202 as the starter 1200, pressurized fluid is supplied at the precooler outlet 516 via an auxiliary unit (e.g., outside the aircraft 100). The pressurized fluid flows to the precooler inlet 514 (e.g., via precooler bypass 528) and then via the PR manifold 510 to the turbine outlet 254. Fluid flows through the PR turbine 250 and exits via an exhaust port 1202 controlled by an exhaust valve 1204 (e.g., a shut-off valve). When the exhaust valve 1204 is in the open position, the exhaust port 1202 provides an auxiliary outlet to allow airflow from the PR turbine 250 to exit via the exhaust port 1202. When the PR turbine 250 operates as the starter, the first control valve 534, the second control valve 536, the third control valve 538, and the fourth control valve 540 are all in the closed position.

[0089] Figure 13 This is a schematic diagram of an aircraft engine 110 and bleed air system 1302 implemented using another exemplary power recovery system 1304 disclosed herein. The components of the exemplary aircraft engine 1300, bleed air system 1302, and power recovery system 1032 are substantially similar to or identical to the combinations described above. Figures 1 to 12The exemplary aircraft engine 110, bleed air system 200, and power recovery system 200 components are shown below, and components having substantially similar or identical functions to those components will not be described in detail below. Instead, interested readers can refer to the corresponding descriptions above. To facilitate this process, similar figure numbers will be used for similar structures. For example, aircraft engine 1300 is substantially the same as aircraft engine 110 and includes fan 206, first bleed air port 242, second bleed air port 244, ECS 236, TAI 238, precooler 256, etc.

[0090] For example, the bleed air system 1300 is essentially the same as the bleed air system 200 and includes a first TAI channel 502, a second TAI channel 504, a low-pressure power recovery (LPPR) channel 506, a high-pressure power recovery (HPPR) channel 508, a PR channel 509, a power recovery (PR) manifold 510, a main manifold 512, a precooler inlet 514, a precooler outlet 516, a first control valve 534, a second control valve 536, a third control valve 538, and a fourth control valve 539. Four control valves 540, a fifth control valve 542, a sixth control valve 546, a seventh control valve 548, one or more sensors 552-566, a bleed air system controller 500, the bleed air system controller 500 including a bleed air regulator 570, a power recovery determiner 572, a power recovery operator 574, a valve operator 576, a precooler operator 578, an input / output (I / O) module 580, and a comparator 582 communicatively coupled via a bus 584, etc.

[0091] For example, the energy recovery system 1304 is basically similar to Figures 2 to 12The illustrated power recovery system 202 includes a power recovery (PR) turbine 250 that receives bleed air via a turbine inlet 252 (i.e., bleed air inlet) and discharges the bleed air to a precooler 256 (e.g., a heat exchanger) via a turbine outlet 254 (e.g., bleed air outlet). An LPPR passage 506 fluidly couples a first bleed air port 242 to the turbine inlet 252, and an HPPR passage 508 fluidly couples a second bleed air port 244 to the turbine inlet 252. A PR passage 509 fluidly couples LPPR 506 and HPPR 508 to the turbine inlet 252. A power recovery (PR) manifold 510 fluidly couples the turbine outlet 254 to the precooler 256. A main manifold 512 fluidly couples to the first bleed air port 242 via the LPPR passage 506 and to the second bleed air port 244 via the HPPR passage 508. The precooler 256 includes a precooler inlet 514 and a precooler outlet 516. The precooler inlet 514 is used to receive bleed air from the PR manifold 510 and / or the main manifold 512. The precooler outlet 516 is fluidly coupled to the ECS 236 via the ECS channel 518 and to other systems 240 via the auxiliary channel 520.

[0092] The PR turbine 250 of the power recovery system 1304 can be operatively (e.g., mechanically) coupled to an auxiliary power unit or machine 1306. The auxiliary power unit 1306 is a shaft-driven device or machine. In other words, the auxiliary power unit 1306 absorbs power supplied via the input shaft of the power absorber. The PR output shaft 304 ( Figure 3 The auxiliary power unit 1306 transmits power to its input shaft 1308 (e.g., driven shaft, generator shaft, etc.). In other words, the input shaft 1308 receives power from the output shaft 304 of the PR turbine 250 (e.g., when the power recovery system 1304 is active). The PR turbine 250 can be operatively coupled to the auxiliary power unit 1306 via a transmission 1310. For example, the transmission 1310 may include a gearbox (e.g., Figure 3 The gearbox 306 shown), gear train (e.g., Figure 3 The gear system 310 shown), and the clutch (e.g., Figure 3The clutch 318 shown) and / or any other transmission (e.g., a fixed-ratio transmission, a continuously variable transmission, etc.). The auxiliary power unit 1306 may include, for example, a generator (e.g., a generator or alternator for generating electricity), a compressor, a turbine, an auxiliary power unit (APU), and / or any other shaft drive that can receive or use energy from the PR turbine 250. The auxiliary power unit 1306 may be located in the engine nacelle of the aircraft engine 1300, the wing box of the wing, the fuselage of the aircraft, and / or any other location. LPPR 506, HPPR 508, PR channel 509, and power recovery (PR) manifold 510 may be routed to the location of the PR turbine 250.

[0093] In operation, the aircraft engine 1300, bleed air system 1302, and power recovery system 1304 are basically similar. Figures 1 to 12 The operation of the aircraft engine 110, bleed air system 200, and power recovery system 202 is shown. For example, the power recovery system 1304 extracts or harvests energy from the engine bleed air via the controller 500 of the bleed air system 1302. Specifically, the PR turbine 250 generates power while processing the bleed air from the turbine inlet 252 to the turbine outlet 254 and transmits the generated power to the aircraft (e.g., Figure 1 The auxiliary power unit 1302 of the aircraft 100 shown. For example, when bleed air flows between turbine inlet 252 and turbine outlet 254, the PR turbine 250 extracts or harvests energy by reducing one or more parameters of the bleed air (e.g., temperature, pressure, etc.). The energy extracted from the bleed air is converted into power (e.g., shaft horsepower) and transmitted (e.g., feedback) to the auxiliary power unit 1306 via the PR turbine 250. In some examples, the power recovery system 1304 extracts energy from the bleed air during predetermined operating states of the aircraft (e.g., taxiing, takeoff, climb, cruise, descent, landing, etc.). Further details of the operation of the bleed air system 1304 are not described further; interested readers can refer to [reference needed]. Figures 1 to 12 and Figure 14 The description.

[0094] The foregoing examples of power recovery systems 202 and 1304 can be employed in aircraft and / or aircraft engines. Although each exemplary power recovery system disclosed above has certain features, it should be understood that a particular feature of one example is not necessarily specific to that example. Rather, any feature described above and / or depicted in the accompanying drawings, in addition to or replacing any other feature of those examples, can be combined with any example. Features of one example are not mutually exclusive with features of another example. Rather, the scope of this disclosure covers any combination of any features. For example, an aircraft engine can employ one or more power recovery systems 202 and 1304. In some examples, an aircraft engine can employ power recovery system 202 and power recovery system 1304. In some examples, aircraft engine 1300 can be used as a starter (e.g., Figure 12 The starter shown is 1200.

[0095] Figure 14 This is a flowchart illustrating an exemplary method 1400, which can be used... Figure 2 The air intake system 200 shown Figure 13 The illustrated air intake system 1302 and / or such as Figures 5 to 13 The control system of the bleed air system controller 500 shown is implemented. For the purposes of discussion, Figure 14 The exemplary method 1400 shown combines Figures 2 to 12 The air intake system 200 shown is... Figure 13 The air intake system 1302 shown is Figures 5 to 13 The air intake system controller 500 shown is used for description. In this way, Figure 14 Each exemplary operation of the exemplary method 1400 shown is implemented through Figures 5 to 13 The illustrated example demonstrates an exemplary manner in which one or more blocks of an exemplary bleed air system controller 500 perform one or more corresponding operations. In this example, the method can be implemented using machine-readable instructions, which include instructions for use by, for example… Figure 15 The processor 1500 shown in the image executes the program. Machine-readable instructions can be one or more executable programs or part of an executable program for execution by a computer processor, such as those combined below. Figure 15 The processor 1512 shown in the exemplary processor platform 1500 discussed herein. Programs may be presented in software stored on non-transitory computer-readable storage media such as CD-ROMs, floppy disks, hard disks, DVDs, Blu-ray discs, or memory associated with the processor 1512; however, the entire program and / or portions thereof may alternatively be executed by a device other than the processor 1512 and / or presented in firmware or dedicated hardware. Furthermore, although references... Figure 14The flowchart shown illustrates an exemplary procedure, but alternatively, many other methods can be used to implement the exemplary bleed air system controller 500. For example, the execution order of the blocks can be changed, and / or some of the described blocks can be modified, eliminated, or combined. Additionally or alternatively, any or all blocks can be implemented by one or more hardware circuits (e.g., discrete and / or integrated analog and / or digital circuits, FPGAs, ASICs, comparators, operational amplifiers (op-amps), logic circuits, etc.) configured to perform the corresponding operations without executing software or firmware.

[0096] The machine-readable instructions described herein can be stored in one or more of the following formats: compressed format, encrypted format, segmented format, compiled format, executable format, packaged format, etc. The machine-readable instructions described herein can be stored as data (e.g., portions of instructions, code, representations of code, etc.) that can be used to create, manufacture, and / or produce machine-executable instructions. For example, machine-readable instructions can be segmented and stored on one or more storage devices and / or computing devices (e.g., servers). Machine-readable instructions may need to be installed, modified, adapted, updated, combined, supplemented, configured, decrypted, decompressed, unpacked, distributed, redistributed, compiled, etc., so that they can be directly read, interpreted, and / or executed by computing devices and / or other machines. For example, machine-readable instructions can be stored in multiple parts that are individually compressed, encrypted, and stored on separate computing devices, wherein these parts, when decrypted, decompressed, and combined, form a set of executable instructions that implement a program such as that described herein.

[0097] In another example, machine-readable instructions may be stored in a state in which they can be read by a computer, but libraries (e.g., dynamic link libraries (DLLs)), software development kits (SDKs), application programming interfaces (APIs), etc., need to be added to execute the instructions on a specific computing device or other device. In yet another example, the machine-readable instructions and / or corresponding programs may need to be configured (e.g., storage settings, data input, recording network addresses, etc.) before they can be fully or partially executed. Therefore, the disclosed machine-readable instructions and / or corresponding programs are intended to cover such machine-readable instructions and / or programs without regard to the specific format or state of the machine-readable instructions and / or programs when stored or otherwise at rest or in transit.

[0098] The machine-readable instructions described in this article can be represented by any past, present, or future instruction language, scripting language, programming language, etc. For example, machine-readable instructions can be represented using any of the following languages: C, C++, Java, C#, Perl, Python, JavaScript, Hypertext Markup Language (HTML), Structured Query Language (SQL), Swift, etc.

[0099] As mentioned above, Figure 13 The exemplary methods shown can be implemented using executable instructions (e.g., computer and / or machine-readable instructions) stored on non-transitory computer and / or machine-readable media such as hard disk drives, flash memory, read-only memory, optical disks, digital universal disks, caches, random access memory, and / or any other storage devices or storage disks, wherein information is stored for any period of time (e.g., extended time periods, permanent, transient instances, temporary buffers, and / or caches of information). As used herein, the term non-transitory computer-readable media is explicitly defined to include any type of computer-readable storage device and / or storage disk, excluding propagation signals and transmission media.

[0100] Go to details Figure 14 The bleed air system controller 500 monitors, receives, and / or otherwise obtains measurements of the pressure of the bleed air in the bleed air system 200 (block 1402). For example, to monitor system parameters, the bleed air system controller 500 receives one or more signals from sensor 552 via I / O module 580.

[0101] The bleed air system controller 500 retrieves, receives, and / or otherwise obtains the target pressure (block 1404). For example, the bleed air regulator 570 retrieves the target pressure from the database 586.

[0102] The bleed air system controller 500 determines whether to activate the power recovery system 202 based on the measured pressure and the target pressure (block 1406). In some examples, to determine whether to activate the power recovery system 202, the power recovery determiner 572 determines via comparator 582 whether the measured pressure is greater than the target pressure to determine whether the PR turbine 250 can add power (e.g., 575 horsepower) to the HPC shaft 224 (block 1404). For example, the power recovery determiner 572 determines whether the PR turbine 250 can add power to the HPC shaft 224 and achieve minimum ECS pressure based on turbine performance maps (e.g., retrieved from database 586), the measured speed (e.g., RPM) of the HPC shaft 224, and the pressure measured from sensor 552. In some examples, the PR turbine 250 determines the pressure difference between the pressure at the turbine inlet 252 and the pressure at the turbine outlet 254 to determine whether the pressure difference is sufficient to provide the required mass flow rate to the ECS 236. In some examples, to determine whether to activate the energy recovery system 1304, the energy recovery determiner 572 determines, via comparator 582, whether the measured pressure is greater than a target pressure to determine whether the PR turbine 250 can add power (e.g., 575 horsepower) to the auxiliary power unit 1306 (block 1404). For example, the energy recovery determiner 572 determines whether the PR turbine 250 can add power to the auxiliary power unit 1306 and achieve the minimum ECS pressure based on a turbine performance map (e.g., retrieved from database 586) and pressure measurements from sensor 552. In some examples, to determine whether to activate the energy recovery system 202 or the energy recovery system 1304, the energy recovery determiner 572 determines whether the PR turbine 250 can provide the minimum ECS pressure based on a turbine performance map (e.g., retrieved from database 586) and pressure measurements from sensor 552.

[0103] If the bleed air system controller 500 determines that the power recovery system 202 or power recovery system 1302 (block 1408) is not activated, the bleed air system controller 500 prevents bleed airflow to the PR turbine 250 (block 1408). For example, the power recovery determiner 572 and / or valve operator 576 move the third control valve 538 to the closed position. In some examples, the power recovery determiner 572 determines that the power recovery system 202 is not activated in response to determining that the PR turbine 250 cannot add power to the HPC shaft 224 or auxiliary power unit 1306. In some examples, if the PR turbine 250 cannot provide the minimum ECS pressure based on the turbine performance chart (e.g., retrieved from database 586) and the pressure measured from sensor 552, the power recovery determiner 572 determines that the power recovery system 202 or power recovery system 1304 is not activated.

[0104] If, at block 1408, the bleed air system controller 500 determines to activate either power recovery system 202 or power recovery system 1304, then the bleed air system controller 500 allows bleed airflow to be directed toward the PR turbine 250 (block 1410). For example, the power recovery determiner 572 and / or valve operator 576 moves the third control valve 538 to the open position to allow bleed airflow to the turbine inlet 252. In some examples, the power recovery determiner 572 determines to activate power recovery system 202 in response to determining that the PR turbine 250 can add power to the HPC shaft 224. In some examples, the power recovery determiner 572 determines to activate power recovery system 1304 in response to determining that the PR turbine 250 can add power to the auxiliary power unit 1306.

[0105] The bleed air system controller 500 engages clutch 318 (block 1412). For example, the power recovery operator 574 adjusts (e.g., modulates) the variable inlet guide vane 320 to increase the output speed of the PR turbine 250 to engage clutch 318.

[0106] The bleed air system controller 500 determines the turbine discharge pressure at turbine outlet 254 (block 1414). For example, the power recovery determiner 572 compares the measured pressure of the bleed air from sensor 556 with a target pressure retrieved from database 586. Based on the comparison between the measured pressure and the target pressure, the bleed air system controller 500 determines whether the turbine discharge pressure is within a threshold range of the target pressure (block 1416). If the discharge pressure is within the threshold range at block 1416, the power recovery operator 574 adjusts (e.g., increases or decreases) the output torque of the PR turbine 250 by adjusting (e.g., increasing or decreasing) the variable inlet guide vanes 320 (block 1418).

[0107] If, at block 1416, the bleed air system controller 500 determines that the turbine discharge pressure is not within the threshold range of the target pressure, then the bleed air system controller 500 determines whether the power recovery turbine discharge temperature at turbine outlet 254 exceeds the maximum temperature threshold (block 1420). For example, the bleed air system 200 measures the discharge temperature of the bleed air at turbine outlet 254 and compares the measured temperature with the maximum temperature threshold or range via comparator 582.

[0108] The bleed air system controller 500 determines whether the turbine discharge temperature exceeds a maximum temperature threshold (block 1422). If, at block 1422, the bleed air system controller 500 determines that the turbine discharge temperature exceeds the maximum temperature threshold, then the bleed air system controller 500 activates the precooler 256 (block 1424). For example, the precooler operator 578 measures the temperature of the bleed air at the precooler outlet 516 via sensor 566 and compares the measured temperature with a target temperature or range. For example, the precooler operator 578 and / or valve operator 576 cause actuator 532 to move precooler valve 530 to a first position to allow bleed air to flow through heat exchanger section 522, and command fan valve 550 to move to an open position to allow cooling fluid through precooler 256 to flow between cooling fluid inlet 524 and cooling fluid outlet 526. For example, the precooler operator 578 adjusts fan valve 550 such that the bleed air at precooler outlet 516 is within the target temperature threshold.

[0109] If, at block 1422, the bleed air system controller 500 determines that the turbine discharge temperature does not exceed the maximum temperature threshold, then the bleed air system controller 500 determines whether the discharge temperature is below the minimum temperature threshold (block 1426). If, at block 1426, the discharge temperature is not below the minimum temperature threshold, then the bleed air system controller 500 allows bleed air to flow through the precooler bypass 528 (block 1428). If, at block 1426, the bleed air system controller 500 determines that the turbine discharge temperature is below the minimum temperature threshold, then the bleed air system controller 500 disables the power recovery system 202 (block 1430). For example, the power recovery operator 574 moves the third control valve 538 to the closed position to prevent bleed air from flowing towards the turbine inlet 252.

[0110] In some examples, the bleed air system controller 500 determines whether to persist and / or otherwise continue monitoring of the power recovery system 202 or the power recovery system 1304 (block 1432). For example, if the aircraft engine 110 is running, the bleed air system controller 500 may determine to stop monitoring of the power recovery system 202 or the power recovery system 1304 based on user input and continuous communication received from sensors communicatively coupled to the bleed air system 200 (e.g., communication heartbeat signals, sensor information, etc.).

[0111] Figure 15 This is a block diagram of an exemplary processor platform 1500, which is configured to execute... Figure 13 The instructions shown are for implementing Figure 15 The illustrated air intake system controller 500. The processor platform 1500 can be, for example, a server, personal computer, workstation, self-learning machine (e.g., neural network), mobile device (e.g., mobile phone, smartphone) or any other type of computing device.

[0112] The processor platform 1500 shown in the example includes a processor 1512. The processor 1512 shown in the example is hardware. For example, the processor 1512 can be implemented by one or more integrated circuits, logic circuits, microprocessors, GPUs, DSPs, or controllers from any desired series or manufacturer. The hardware processor can be a semiconductor-based (e.g., silicon-based) device. In this example, the processor implements a bleed air regulator 570, a power recovery determiner 572, a power recovery operator 574, a valve operator 576, a precooler operator 578, a comparator 582, and an I / O module 580.

[0113] The processor 1512 of the illustrated example includes local memory 1513 (e.g., cache). The processor 1512 of the illustrated example communicates via bus 1518 with main memory, which includes volatile memory 1514 and non-volatile memory 1516. Volatile memory 1514 may be implemented using synchronous dynamic random access memory (SDRAM), dynamic random access memory (DRAM), RAMBUS® dynamic random access memory (RDRAM®), and / or any other type of random access memory device. Non-volatile memory 1516 may be implemented using flash memory and / or any other desired type of memory device. Access to main memory 1514, 1516 is controlled by a memory controller.

[0114] The processor platform 1500 shown in the example also includes interface circuitry 1520. Interface circuitry 1520 can be implemented using any type of interface standard, such as an Ethernet interface, Universal Serial Bus (USB), Bluetooth® interface, Near Field Communication (NFC) interface, and / or PCI express interface.

[0115] In the example shown, one or more input devices 1522 are connected to interface circuitry 1520. Input devices 1522 allow users to input data and / or commands into processor 1512. Input devices can be implemented, for example, keyboards, buttons, mice, touchscreens, touchpads, trackballs, isopoints, and / or voice recognition systems.

[0116] One or more output devices 1524 are also connected to the interface circuitry 1520 of the illustrated example. The output devices 1524 may be implemented, for example, via display devices (e.g., light-emitting diodes (LEDs), organic light-emitting diodes (OLEDs), liquid crystal displays (LCDs), cathode ray tube displays (CRTs), in-situ switch (IPS) displays, touchscreens, etc.), haptic output devices, and / or speakers. Therefore, the interface circuitry 1520 of the illustrated example typically includes a graphics driver card, a graphics driver chip, and / or a graphics driver processor.

[0117] The interface circuit 1520 of the example shown also includes communication devices, such as a transmitter, receiver, transceiver, modem, residential gateway, wireless access point, and / or network interface, to facilitate data exchange with external machines (e.g., any kind of computing device) via network 1526. Communication can be via, for example, Ethernet connections, digital subscriber line (DSL) connections, telephone line connections, coaxial cable systems, satellite systems, fieldline wireless systems, cellular telephone systems, etc.

[0118] The processor platform 1500 shown in the example also includes one or more mass storage devices 1528 for storing software and / or data. Examples of such mass storage devices 1528 include floppy disk drives, hard disk drives, optical disk drives, Blu-ray disc drives, redundant array of independent disks (RAID) systems, and digital multifunction disk (DVD) drives.

[0119] Figure 15 The machine-executable instructions (coded instructions) 1532 shown may be stored in a mass storage device 1528, volatile memory 1514, non-volatile memory 1516, and / or on a removable, non-transitory computer-readable storage medium such as a CD or DVD.

[0120] "Including" and "comprising" (and all their forms and tenses) are used herein as open-ended terms. Therefore, whenever a technical solution adopts any form of "include" or "comprise" (e.g., includes, includes, comprising, including, having, etc.) as a preamble or in any kind of technical solution description, it should be understood that additional elements, terms, etc., may be present that do not fall outside the scope of the corresponding technical solution or description. As used herein, when the phrase "at least" is used as a transitional term in, for example, the preamble of a technical solution, it is open-ended in the same way that the terms "comprising" and "including" are open-ended. When used, for example, in the form of A, B, and / or C, the term "and / or" refers to any combination or subset of A, B, C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, and (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A or B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B.

[0121] As used herein, singular references (e.g., "a(a)", "an(an)", "first", "second", etc.) do not exclude multiple entities. As used herein, the term "a" or "an" refers to one or more of that entity. The terms "a(a)" (or "an(an)"), "one or more", and "at least one" are used interchangeably herein. Furthermore, although listed separately, multiple apparatuses, elements, or method actions can be implemented by, for example, a single unit or processor. Additionally, although individual features may be included in different examples or technical solutions, these features can be combined, and inclusion in different examples or technical solutions does not imply that the combination of features is infeasible and / or disadvantageous.

[0122] At least some of the foregoing examples include one or more features and / or advantages, including but not limited to the following: In some examples, the power recovery system for an aircraft engine includes a power recovery turbine coupled to a shaft drive unit. A bleed air valve is coupled between the power recovery turbine and a bleed air source. A controller is configured to operate the bleed air valve to allow bleed air to flow towards the power recovery turbine when the aircraft engine is operating in a predetermined operating mode.

[0123] In some examples, the shaft drive is the aircraft’s core engine, which includes a core compressor, a core turbine, and a spindle, with the power recovery turbine operatively coupled to the spindle of the core engine.

[0124] In some examples, the output shaft of the power recovery turbine is operatively coupled to the spindle via a transmission.

[0125] In some examples, the transmission includes a clutch coupled between the power recovery turbine and the core engine, the clutch being configured to operatively couple the output shaft and the spindle when the aircraft engine is operating in a predetermined operating mode, and to operatively disengage the output shaft and the spindle when the aircraft engine is not operating in the predetermined operating mode.

[0126] In some examples, the shaft drive is a generator with an input shaft, wherein the output shaft of the power recovery turbine is coupled to the input shaft of the generator.

[0127] In some examples, the predetermined operating mode includes at least one of takeoff, climb, descent, landing, or cruise.

[0128] In some examples, the power recovery turbine includes a turbine inlet and a turbine outlet, with the turbine inlet fluidly coupled to a bleed air source and the turbine outlet fluidly coupled to a heat exchanger.

[0129] In some examples, the power recovery turbine includes variable nozzle guide vanes, and the controller is configured to adjust the variable nozzle guide vanes to regulate the exhaust pressure of the bleed air at the turbine outlet.

[0130] In some examples, the power recovery system includes a power recovery turbine having: a bleed air inlet for receiving bleed air from a bleed air source; a bleed air outlet for supplying bleed air to downstream systems; and an output shaft operatively coupled to the input shaft of an aircraft shaft drive. The power recovery turbine generates power in response to processing the bleed air as it flows from the bleed air inlet to the bleed air outlet, and transmits the generated power to the input shaft via the output shaft.

[0131] In some examples, a transmission is used to couple the output shaft of the power recovery turbine to the input shaft of the shaft drive unit.

[0132] In some examples, the transmission includes a clutch to engage the output shaft of the power recovery turbine with the input shaft of the shaft drive and to disengage the output shaft of the power recovery turbine from the input shaft of the shaft drive.

[0133] In some examples, the transmission includes a multi-speed gearbox that reduces the speed of the output shaft of the power recovery turbine to the speed of the input shaft when the power recovery turbine is engaged with the shaft drive.

[0134] In some examples, the precooler is in fluid communication with the bleed air outlet of the power recovery turbine.

[0135] In some examples, the bleed air valve can move between an open position that allows bleed air to flow into the bleed air inlet of the power recovery turbine and a closed position that prevents bleed air from flowing into the bleed air inlet.

[0136] In some examples, a controller is used to control the operation of a bleed valve between an open position and a closed position.

[0137] In some examples, the power recovery turbine includes variable nozzle guide vanes, wherein the exhaust pressure of the bleed air at the bleed air outlet is adjusted by regulating the variable nozzle guide vanes.

[0138] An exemplary aircraft includes an aircraft engine having a core compressor that generates compressed air and a core turbine that drives the core compressor. A power recovery turbine is operatively coupled to the aircraft engine. The power recovery turbine has a turbine inlet in fluid communication with a bleed air supply source provided by the core compressor and a turbine outlet in fluid communication with downstream systems of the aircraft. The power recovery turbine generates power while processing the bleed air from the turbine inlet to the turbine outlet and delivers the generated power to the core compressor of the aircraft engine.

[0139] In some examples, the energy recovery turbine is located inside the aircraft engine.

[0140] In some examples, the precooler is located upstream of the power recovery turbine.

[0141] In some examples, bleed air control valves are used to control the flow of bleed air from the bleed air supply source to the turbine inlet.

[0142] In some examples, the controller is communicatively coupled to the bleed air control valve, and the controller is configured to move the bleed air control valve between an open position that allows bleed air to flow to the turbine inlet and a closed position that prevents bleed air from flowing to the turbine inlet.

[0143] In some examples, the power recovery turbine includes variable nozzle guide vanes, wherein the exhaust pressure of the bleed air at the turbine outlet is adjusted by regulating the variable nozzle guide vanes.

[0144] In some examples, the power recovery turbine may be mechanically or operatively coupled to the shaft drive power unit to receive power generated by the power recovery turbine to drive the input shaft of the shaft drive power unit.

[0145] Although certain exemplary methods, apparatuses, and articles of manufacture have been described herein, the scope of this patent is not limited thereto. Rather, this patent covers all methods, apparatuses, and articles of manufacture that fall entirely within the scope of the appended technical solutions, either literally or under the doctrine of equivalents.

Claims

1. An aircraft power recovery system for aircraft engines, including: A power recovery turbine is coupled to a shaft drive unit, wherein the shaft drive unit is the core engine of the aircraft, the core engine including a core compressor, a core turbine, and a spindle, the power recovery turbine being operatively coupled to the spindle of the core engine, wherein the output shaft of the power recovery turbine is operatively coupled to the spindle via a transmission, wherein the power recovery turbine outputs power via the output shaft, and the power is transmitted to the aircraft engine via the transmission; A bleed air valve, the bleed air valve being coupled between the power recovery turbine and the bleed air source; and A controller configured to operate the bleed air valve to allow bleed air to flow toward the power recovery turbine when the aircraft engine is operating in a predetermined operating mode. The transmission includes a clutch coupled between the power recovery turbine and the core engine. The clutch is configured to operatively couple the output shaft and the spindle when the aircraft engine is operating in the predetermined operating mode, and to operatively discouple the output shaft and the spindle when the aircraft engine is not operating in the predetermined operating mode.

2. The system according to claim 1, wherein, The predetermined operating mode includes at least one of takeoff, climb, descent, landing, or cruise.

3. The system according to claim 1, wherein, The power recovery turbine includes a turbine inlet and a turbine outlet, the turbine inlet being fluidly coupled to the bleed air source and the turbine outlet being fluidly coupled to a heat exchanger.

4. The system according to claim 3, wherein, The power recovery turbine includes variable nozzle guide vanes, and the controller is configured to adjust the variable nozzle guide vanes to adjust the exhaust pressure of the bleed air at the turbine outlet.

5. The system according to claim 1, wherein, The energy recovery turbine also includes: A bleed air inlet, wherein the bleed air inlet is used to receive bleed air from the bleed air source; A bleed air outlet, wherein the bleed air outlet is used to provide bleed air to a downstream system; and An output shaft operatively coupled to the input shaft of the aircraft's shaft drive unit, wherein the power recovery turbine generates power in response to processing the bleed air as it flows from the bleed air inlet to the bleed air outlet, and the power recovery turbine transmits the generated power to the input shaft via the output shaft.

6. A method of operating an aircraft bleed air system for an aircraft engine, the bleed air system comprising a power recovery system, the power recovery system comprising: A power recovery turbine, wherein the power recovery turbine is coupled to a shaft drive device; A bleed air valve, which is coupled between the power recovery turbine and the bleed air source; as well as A controller configured to operate the bleed air valve to allow bleed air to flow toward the power recovery turbine when the aircraft engine is operating in a predetermined operating mode. The method includes: Measure the bleed air pressure within the bleed air system; compare the measured bleed air pressure with the target bleed air pressure; Based on the comparison, the energy recovery turbine is activated, wherein the shaft drive is the core engine of the aircraft, the core engine including a core compressor, a core turbine, and a spindle, the energy recovery turbine being operatively coupled to the spindle of the core engine, wherein the output shaft of the energy recovery turbine is operatively coupled to the spindle via a transmission, wherein the energy recovery turbine outputs power via the output shaft, the power being transmitted to the aircraft engine via the transmission, and wherein the transmission includes a clutch coupled between the energy recovery turbine and the core engine, the clutch being configured to operatively couple the output shaft and the spindle when the aircraft engine is operating in the predetermined operating mode, and to operatively discouple the output shaft and the spindle when the aircraft engine is not operating in the predetermined operating mode.

Images