System for selectively transmitting power in a turbine engine

Abstract

To provide a system configured to be operatively connected to a turbine engine of an aircraft and an accessory of the aircraft to provide efficient operation of the turbine engine.SOLUTION: The system 15 is configured to selectively transfer power between the first pressure spool 75 of the turbine engine 20 and the second pressure spool 85 of the turbine engine to power the accessory 60 to supply air to an aircraft system of the aircraft.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001]

[0001] The present disclosure relates generally to the field of turbine engines, and more particularly to a system for selectively providing selective transmission of mechanical power in a turbine engine. [Background technology]

[0002]

[0002] Various aircraft are powered by turbine engines. These engines include a fan that provides a significant portion of the thrust for the overall propulsion system. The engine core generates additional thrust by driving the fan and directing the exhaust aft. In addition to providing thrust to propel the aircraft, the turbine engine also provides power to aircraft systems in the form of shaft power and pneumatic bleed air.

[0003]

[0003] When an aircraft is on the ground with the engine running at idle, the turbine engine provides shaft power for the aircraft's operation. Shaft power is typically extracted from the engine's core shaft (also called the N1 or high spool). Extracting shaft power from the high spool during ground operation increases ground idle fuel flow and reduces the stability margin of the high-pressure compressor.

[0004]

[0004] The turbine engine may also be configured to provide pneumatic bleed air to aircraft systems, including one or more components such as, but not limited to, an environmental control system for pressurizing the aircraft's passenger cabin and a thermal anti-icing system for providing heated air for anti-icing applications. The supply of air to the aircraft systems is typically provided by bleed air drawn from the turbine engine's high-pressure compressor.

[0005] Alternatively, the aircraft's pneumatic bleed air may be provided by an auxiliary compressor using shaft power and air from a lower stage of the engine compressor, the auxiliary compressor operating to provide air to the aircraft systems at the required pressure levels.

[0006]

[0006] What is needed is a system for providing efficient operation of a turbine engine. Summary of the Invention

[0007] One aspect is directed to a system configured to be operatively connected to an aircraft turbine engine and an aircraft accessory, the system configured to selectively transfer power between a first pressure spool of the turbine engine and a second pressure spool of the turbine engine to power the accessory.

[0008]

[0008] In another aspect, a system includes a transmission having a gearbox and a clutch.

[0009] In another aspect, a transmission is configured to selectively operate in one of a first configuration, a second configuration, and a third configuration. The first configuration transfers power from the turbine engine to the accessory. The second configuration transfers power from the first pressure spool to the second pressure spool. The third configuration prevents transfer of power from the turbine engine to the accessory and prevents transfer of power from the first pressure spool to the second pressure spool.

[0010] In another aspect, in the first configuration, the transmission is powered by the second pressure spool.

[0011]

[0011] In another aspect, the system further includes a transmission, a first drive mechanism connecting the first pressure spool to the transmission, and a second drive mechanism connecting the second pressure spool to the transmission.

[0012]

[0012] In another aspect, the accessory is a compressor and the transmission is configured to operate at different speeds to cause the compressor to supply air at a desired pressure to an aircraft system of the aircraft.

[0013]

[0013] In another aspect, a controller having a processing circuit is configured to drive an accessory and transmit power generated from the first pressure spool to the second pressure spool.

[0014]

[0014] In another aspect, the controller is integrated within the body of the transmission.

[0015] In another aspect, the controller is further configured to operate one or more components of an aircraft system of the aircraft.

[0016]

[0016] In another aspect, the transmission is configured to transmit power from a first pressure spool to a second pressure spool and to transmit power from the second pressure spool to the first pressure spool.

[0017] In another aspect, the transmission is powered by a first pressure spool.

[0018]

[0018] In another embodiment, the accessory is a compressor, the first pressure spool is a low pressure spool, and the second pressure spool is a high pressure spool, and the system is configured to selectively transfer power between the low pressure spool and the high pressure spool to supply air to an aircraft system of the aircraft.

[0019] One aspect is directed to a system configured to be operatively connected to a turbine engine of an aircraft. The system includes an accessory, a transmission, a first drive mechanism connecting the transmission to a second pressure spool of the turbine engine, and a second drive mechanism connecting the transmission to the first pressure spool of the turbine engine. The transmission is configured to transfer power of the turbine engine via the first drive mechanism and the second drive mechanism. The transmission is configured to drive the accessory.

[0020] In another aspect, a transmission is configured to transfer power from a first pressure spool to a second pressure spool via a first drive mechanism and a second drive mechanism.

[0021] In another aspect, a transmission is configured to transfer power from the second pressure spool to the first pressure spool via a first drive mechanism and a second drive mechanism.

[0022]

[0022] In another aspect, a transmission includes a gearbox operatively connected to and powered by the second pressure spool, and a clutch.

[0023]

[0023] In another aspect, the transmission is a continuously variable transmission.

[0024] In another aspect, a transmission includes a gearbox operatively connected to and powered by a first pressure spool.

[0025] In another aspect, the accessory is a compressor and the system includes a bleed air system including one or more ports and a first passageway through which air is supplied from the turbine engine to the aircraft.

[0026] In another aspect, the bleed air system further comprises a second passageway supplying air from the turbine engine to the compressor, the second passageway being separate from the first passageway.

[0027]

[0027] In another aspect, the controller is configured to selectively operate the transmission in a first mode for transmitting turbine engine power via the first drive mechanism and the second drive mechanism and in a second mode for driving an accessory.

[0028]

[0028] In another aspect, the controller is further configured to control operation of a bleed air system that supplies air from the turbine engine to the aircraft.

[0029] One aspect is directed to a method of transmitting mechanical power in a turbine engine of an aircraft, the method including: positioning a transmission in a first configuration to transmit power from the turbine engine to an accessory; and positioning the transmission in a second configuration to transmit power from a first pressure spool of the turbine engine to a second pressure spool of the turbine engine.

[0030]

[0030] In another aspect, the method further includes the accessory being a compressor, transmitting power from the turbine engine to the compressor, and supplying air from the turbine engine to an aircraft system.

[0031]

[0031] In another aspect, the first pressure spool is a low pressure spool and the second pressure spool is a high pressure spool, and positioning the transmission in the second configuration includes transmitting power from the low pressure spool of the turbine engine to the high pressure spool of the turbine engine.

[0032] In another aspect, the method further includes providing air to the aircraft system via a bleed air system when the transmission is in the first configuration.

[0033] In another aspect, the method further includes preventing power from being transferred from the turbine engine to the accessory in the second configuration.

[0034] In another aspect, the second pressure spool is a high pressure spool, and the method further includes transmitting power from the high pressure spool of the turbine engine to the accessory in the first configuration.

[0035] In another aspect, the method further includes placing the transmission in a third configuration and transmitting power from the high pressure spool to the low pressure spool.

[0036]

[0036] The above-described features, functions, and advantages can be realized alone in various aspects or can be combined in further multiple aspects, details of which can be confirmed by referring to the following description and accompanying drawings. [Brief explanation of the drawings]

[0037] [Figure 1]

[0037] FIG. 1 is an isometric view of an aircraft having a turbine engine. [Figure 2]

[0038] 1 is a schematic diagram of a system for selectively transmitting mechanical power of a turbine engine; [Figure 3]

[0039] 1 is a schematic diagram of a system for supplying air to an aircraft system and transmitting power within a turbine engine. [Figure 4]

[0040] 1 is a schematic diagram of a system for selectively transmitting mechanical power of a turbine engine; [Figure 5]

[0041] FIG. 2 is a schematic diagram of a controller. [Figure 6]

[0042] FIG. 1 is a schematic diagram of a controller configured to operate components to provide air to an aircraft system and to transmit power within a turbine engine. [Figure 7]

[0043] 1 is a flowchart of a method of operating a transmission to selectively transmit mechanical power of a turbine engine. DETAILED DESCRIPTION OF THE INVENTION

[0038]

[0044] 1 illustrates one embodiment of an aircraft 100. The aircraft 100 generally includes a fuselage 103 and wings 101. One or more turbine engines 20 are mounted to the wings 101 to propel the aircraft 100. A cockpit 102 is located forward of the fuselage 103 and includes controls for operating the aircraft 100. The aft section of the fuselage 103 includes a cabin area configured to accommodate passengers or cargo.

[0039]

[0045] The aircraft 100 includes aircraft systems 110. The aircraft systems 110 include one or more systems for operating various components, including, but not limited to, an environmental control system, a wing anti-icing system, an engine anti-icing system, and various other components that utilize heated and / or pressurized air. One or more of the turbine engines 20 provide bleed air to the aircraft systems 110 for use by one or more of the components, such as in the environmental control system. The bleed air may be provided during various operating conditions, such as, but not limited to, ground operation (taxiing), takeoff or climb, cruise, holding, and descent.

[0040]

[0046] The engines 20 provide thrust to propel the aircraft and power the aircraft's hydraulic and pneumatic systems. The engines 20 also provide shaft power to the aircraft electrical systems, including aircraft systems 110, aircraft computers, motor-driven hydraulic pumps, and / or other motors and electrical devices and accessories.

[0041]

[0047] Increased demand for aircraft accessory power increases the need to operate turbine engine 20 at higher idle speeds. More specifically, increasing engine idle speed allows the increased power demand to be met without sacrificing compressor stall margin. However, increased idle speed may also produce higher than desired thrust levels for turbine engine 20 during both flight idle descent and / or ground idle operations. Over time, continued operation at increased thrust levels during such idle operations may increase aircraft brake maintenance costs, and the increased fuel flow may directly increase aircraft operating costs.

[0042]

[0048] The present application is directed to a system 15 that transfers power from turbine engines 20 for efficient operation of an aircraft 100. In some embodiments, the engines 20 are configured to provide power to accessories. In some embodiments, a first of the engines 20 operates to propel the aircraft 100, generate power, and provide bleed air. In some embodiments, two or more of the turbine engines 20 operate to generate power and provide bleed air, and thus include the same components and operate in the same manner. The following disclosure includes the operation of a single turbine engine 20. It is understood that two or more of the engines 20 may operate in substantially the same manner to provide power transfer to meet the demands of the aircraft 100.

[0043]

[0049] 2 , the system for transmitting power 15 includes a transmission 30 configured to selectively transmit power from the turbine engine 20. The transmission 30 is configured to transmit power to an accessory 60. The transmission 30 is also configured to transmit power within the turbine engine 20.

[0044]

[0050] Accessories 60 may include a variety of different devices, such as various airframe accessories and various engine accessories. One example includes a compressor that is driven to provide air to aircraft 100. Other examples of accessories 60 include, without limitation, generators, hydraulic pumps, fuel pumps, and oil pumps.

[0045]

[0051] Some of the embodiments disclosed below include an accessory 60 that is a compressor. However, a compressor is only one example of a variety of devices that may be powered via the configurations disclosed in this application.

[0046]

[0052] System 15 solves two problems associated with conventional aircraft. The first problem solved is that bleed air is often inefficient due to the turbine engine providing air at a higher pressure than required by the aircraft systems. The second problem solved is that the engine operates at higher than desired idle levels, especially at ground idle.

[0047]

[0053] 3 illustrates a schematic diagram of a turbine engine 20 and its architecture for transmitting power and supplying air to an aircraft system 110. The turbine engine 20 includes a fan 21 that draws air into a fan duct or compressor intake section and into a compressor 22. The compressor 22 includes one or more compressor sections. In some embodiments, as shown in FIG. 3, the compressor 22 is a twin-shaft compressor 22 that includes a low-pressure compressor 70 and a high-pressure compressor 80. In some embodiments, the low-pressure compressor 70 and the high-pressure compressor 80 include various compressor stages that progressively increase the pressure of the air as it flows from the input section of the fan 21 to the combustor 25.

[0048]

[0054] The low-pressure compressor 70 is operably coupled to a low-pressure shaft 71, and the high-pressure compressor 80 is operably coupled to a high-pressure shaft 81. The low-pressure shaft 71 is further coupled to a low-pressure turbine 72, and the high-pressure shaft 81 is coupled to a high-pressure turbine 82. In this embodiment, the compressor 22 is a dual-shaft compressor including two compressors 70, 80. However, in other embodiments, the compressor 22 may include more compressor sections. Each compressor section may have, for example, a turbine and a respective shaft.

[0049]

[0055] After exiting the high-pressure compressor 80, the highly compressed air is provided to the combustor 25, where fuel is injected, mixed with the highly compressed air, and ignited. The high-energy airflow exiting the combustor 25 rotates the blades of the turbines 72, 82, which are coupled to respective ones of the shafts 71, 81. The rotation of the shafts 71, 81 rotates the blades of the compressors 70, 80. The heated air is exhausted through a nozzle, where it mixes with cooler air provided by the fan 21, which bypasses the engine core, to generate forward thrust.

[0050]

[0056] Low-pressure components including low-pressure compressor 70, low-pressure shaft 71, and low-pressure turbine 72 form low-pressure spool 75. High-pressure components including high-pressure compressor 80, high-pressure shaft 81, and high-pressure turbine 82 form high-pressure spool 85. In some embodiments, such as shown in Figure 3, shafts 71, 81 are collinearly aligned, with the first shaft 71 located inside the second shaft 81.

[0051]

[0057] The bleed air system 40 supplies engine bleed air for use by the aircraft system 110. The bleed air system 40 includes one or more ports that draw air from the turbine engine 20. In some embodiments, such as shown in FIG. 3 , the bleed air system 40 includes a first bleed port 41 and a second bleed port 42. The second bleed port 42 is located downstream from the first bleed port 41, such that the pressure of the bleed air provided by the second bleed port 42 is higher than the pressure of the bleed air provided by the first bleed port 41. A passage 43 leads from the ports 41, 42 and may include one or more valves 45 for controlling the flow of air. The valve 45 may include various configurations, including, but not limited to, a one-way valve, a check valve, a pressure regulating valve, and a shut-off valve. The passage 43 leads into a passage 46. In some embodiments, the bleed air provided by the first and second ports 41, 42 is elevated in temperature. The bleed air flows through a precooler 48 to reduce its temperature. The air is output into a passageway 47 and directed to the aircraft systems 110.

[0052]

[0058] Another passage 44 leads from the engine 20 to a compressor 60. In some embodiments, the compressor 60 is a shaft-driven compressor (SDC). The compressor has a high horsepower capacity (e.g., 250 HP, 400 HP) and operates at a specific rotational speed to stay within its operating map. The compressor compresses bleed air received through the passage 44 and supplies the compressed air to the aircraft systems 110 through a passage 49. In some embodiments, the compressor receives bleed air through the passage 44, boosts the bleed air to a higher pressure, and outputs the air through the passage 49 to meet the demands of the aircraft systems 110. One or more valves 45 may be positioned along the passage to control the flow of bleed air.

[0053]

[0059] The transmission 30 transmits power from the turbine engine 20 to operate the accessory 60. The transmission 30 adjusts or controls the gear ratio to drive the accessory 60 at a desired rotational speed. The high-pressure drive 31 and the low-pressure drive 32 transmit power from a high spool 85 of the turbine engine to the transmission 30. The drive mechanisms 31, 32 may include various configurations, such as, but not limited to, shafts, gear trains, and pulleys. In some embodiments, a gearbox (not shown) is connected to the drive mechanisms 31, 32 and the transmission 30. The gearbox includes a drive train with multiple gears to set the speed of the components. The transmission 30, the high-pressure drive 31, and the low-pressure drive 32 mechanically link the low-pressure spool 75 to the high-pressure spool 85. The drive mechanisms 31, 32 may be coupled to the spools 75, 85 in various manners. In some embodiments, the coupling is via a gear train (eg, comprising bevel gears) extending between the ends of the drive mechanisms 31, 32 and the respective spools 75, 85.

[0054]

[0060] In addition to powering the accessories 60, the transmission 30 is also configured to transmit mechanical power within the turbine engine 20. Mechanical power from the excess power available at the low-pressure spool 75 is directed back to the high-pressure spool 85, allowing the required speed of the high-pressure spool 85 to be maintained, but with reduced fuel flow. Furthermore, withdrawing power from the low-pressure spool 75 reduces the rotational speed of the low-pressure spool 75, which in turn reduces the rotational speed of the fan 21. Thus, unnecessary fan thrust is reduced, and the turbine engine 20 can utilize the excess power to operate additional accessories in the aircraft system 110 without increasing fuel flow. As a result, the thrust and fuel flow of the turbine engine 20 are beneficially reduced at idle.

[0055]

[0061] The transfer of power from the low pressure spool 75 to the high pressure spool 85 occurs when the turbine engine 20 is producing excess thrust. The excess thrust is extracted from the low pressure spool 75 to power the high pressure spool 85.

[0056]

[0062] FIG. 4 shows transmission 30 operatively connected to drive mechanisms 31, 32 and accessory 60. Transmission 30 includes a variable speed gearbox 33 for driving accessory 60 at different desired speeds. Transmission 30 also includes a power transfer clutch 34 configured to transfer power from first pressure spool 75 to second pressure spool 85. In some embodiments, transmission 30 also includes a gearbox (not shown) operatively connected to drive mechanisms 31, 32. The gearbox provides for operation of drive mechanisms 31, 32 at various speeds. Transmission 30 can include a variety of different configurations, including, but not limited to, a continuously variable transmission or a transmission with a torque converter. In some embodiments, the transmission includes a fixed speed transmission.

[0057]

[0063] Transmission 30 operates in one of three configurations. The first configuration engages transmission 33 with accessory 60 and transfers power to accessory 60. The second configuration engages power transfer clutch 34 and transfers power between spools 75, 85. The third configuration disengages both transmission 33 and clutch 34 and does not power accessory 60 or transfer power between spools 75, 85.

[0058]

[0064] In some embodiments, the first pressure spool 75 is a low pressure spool and the second pressure spool 85 is a high pressure spool. In other embodiments, the spools 75, 85 have different configurations.

[0059]

[0065] Controller 120 controls the operation of transmission 30. In some embodiments, controller 120 is a separate element that functions solely to control transmission 30. Controller 120 may be located at transmission 30 or may be spaced apart from transmission 30 in another area of ​​aircraft 100. In one embodiment, controller 120 controls the operation of one or more aircraft systems 110 in addition to transmission 30. In other embodiments, controller 120 is included within a larger system (e.g., an aircraft system controller) that performs additional functions. In some embodiments, controller 120 communicates with an engine controller. In some embodiments, controller 120 is part of an engine controller.

[0060]

[0066] Controller 120 operates based on several factors, including one or any combination of the following: the ground speed of aircraft 100, the weight on the wheels of aircraft 100 (e.g., indicating that aircraft 100 is landing), a commanded engine power level as an input from controller 120, or during different stages of aircraft 100 operation. Exemplary stages of aircraft 100 operation that may trigger operation of transmission 30 include ground idle operation of aircraft 100, when aircraft 100 is taxiing, when aircraft 100 is entering takeoff mode, during descent of aircraft 100, or during flight of aircraft 100 to assist in restarting another turbine engine 20. In some embodiments, controller 120 receives signals from one or more other systems (e.g., a flight controller) on aircraft 100 to identify the factors.

[0061]

[0067] FIG. 5 illustrates a controller 120 that operates the transmission 30. The controller 120 is a computing device that includes a processing circuit 121. The processing circuit 121 controls the operation of the transmission 30 according to program instructions 129 stored in a memory circuit 122. The processing circuit 121 includes one or more circuits, a microcontroller, a microprocessor, hardware, or a combination thereof. The memory circuit 122 includes a non-transitory computer-readable storage medium that stores the program instructions 129. The non-transitory computer-readable storage medium configures the processing circuit 121 to perform one or more of the techniques described herein. The memory circuit 122 may include various memory devices, such as, for example, read-only memory and flash memory. The memory circuit 122 may be a separate component as shown in FIG. 5 or may be combined with the processing circuit 121.

[0062]

[0068] Communications circuitry 123 provides communication with one or more of the components, including, but not limited to, transmission 30, accessories 60, turbine engine 20, bleed air system 40, aircraft systems 110, and flight controllers. Communications circuitry 123 is configured for communication over one or more wired and / or wireless communication links. In one particular embodiment, the wired communication links include fiber optic cables. In some embodiments, communications circuitry 123 is configured for communication with one or more remote nodes located remotely from aircraft 100.

[0063]

[0069] User interface 124 is provided for a person, such as a pilot or flight crew member, to monitor and / or control one or more aspects of transmission 30. In some embodiments, user interface 124 is located in cockpit 102 for use during flight. User interface 124 includes one or more input devices 125, such as, but not limited to, a keypad, touchpad, rollerball, and joystick, that provide for commands to be input into processing circuit 121. User interface 124 may also include one or more displays 126 for displaying information.

[0064]

[0070] In some embodiments where accessory 60 is a compressor, a single dedicated controller 120 monitors and / or controls operation of transmission 30 to control power delivery and air supply. In other embodiments, operation occurs via two or more controllers 120. FIG. 6 illustrates a system with various levels of controllers 120. The controllers 120 include a first level controller 120 that includes an engine controller 120a and an air supply controller 120b. A second level controller 120 includes a loop controller 120c and a valve controller 120d. In some embodiments, higher level controllers function to control general aspects of air control and power delivery. Lower level controllers function to control more specific aspects. In the embodiment of FIG. 6, loop controller 120c controls transmission 33, and valve controller 120d controls valve 45 and the compressor.

[0065]

[0071] In some embodiments, operation of transmission 30 to power accessory 60 includes air supply controller 120b commanding a desired speed ratio for gearbox 33. Air supply controller 120b also controls valve 45 and accessory 60. In the power transfer configuration, engine controller 120a controls gearbox 33 to command the desired speed ratio.

[0066]

[0072] 7 illustrates a method of operating the transmission 30. The method includes placing the transmission 30 in a first configuration (block 200), which transmits power from the turbine engine 20 to the accessory 60.

[0067]

[0073] The method also includes placing the transmission 30 in a second configuration (block 202), which transfers power from the first pressure spool 75 to the second pressure spool 85 of the turbine engine 20.

[0068]

[0074] 7 , the method includes placing the transmission 30 in a first configuration to transfer power from the turbine engine 20 to the accessory 60 to supply air to the aircraft system 110. The method also includes placing the transmission 30 in a second configuration to transfer power from a low-pressure spool to a high-pressure spool of the turbine engine 20.

[0069]

[0075] In some embodiments, when transmission 30 is configured to transfer power between first pressure spool 75 and second pressure spool 85, accessory 60 is unavailable when power is being transferred between spools 75, 85. However, the ability to transfer power between spools 75, 85 is generally realized during ground idle, and the two functions of power transfer and accessory 60 do not interfere with each other. In some embodiments, accessory 60 remains engaged during power transfer operation, but the gear ratio is determined by the power transfer operation.

[0070]

[0076] In some embodiments where accessory 60 is a compressor, when accessory 60 is powered, air bleed system 40 does not provide air to aircraft system 110. In other embodiments, both air bleed system 40 and accessory 60 provide air to aircraft system 110 simultaneously.

[0071]

[0077] In some embodiments, engine 20 includes two spools 75, 85 (e.g., a high spool and a low spool). In other embodiments, engine 20 includes one or more intermediate pressure spools that provide for power transfer from a lower pressure spool to a higher pressure spool (e.g., from an intermediate spool to a high pressure spool, or from a low pressure spool to an intermediate spool).

[0072]

[0078] In some embodiments, the transmission 30 includes a continuously variable transmission. The continuously variable transmission combines the benefits of efficient air delivery of the engine-mounted shaft-driven accessory 60 with the engine operability benefits of power transfer. The shaft-driven compressor concept utilizes a continuously variable transmission to allow the shaft-driven compressor to operate at its required speed while being driven by the second pressure shaft 85. The continuously variable transmission also transfers horsepower from the first pressure spool 75 to the second pressure spool 85. In some embodiments, the potential benefit of this concept is a 2.5% improvement in fuel burn, with 1.5% coming from the efficient air delivery and 1% coming from enabling shaft power transfer.

[0073]

[0079] The term "substantially" in connection with a quantity or measurement means that the recited characteristic, parameter, or value need not be achieved exactly. Rather, deviations or variations (including, for example, tolerances, measurement errors, measurement accuracy limits, and other factors known to those skilled in the art) may occur to the extent that they do not eliminate the effect intended to be produced by the feature.

[0074]

[0080] Aspects disclosed herein apply to many different engine architectures, including, but not limited to, open rotor engines, turboshaft engines, geared turbofan engines, and three-spool engines.

[0075]

[0081] The present disclosure may be practiced otherwise than as specifically set forth herein without departing from the essential characteristics of the invention. The present embodiments are to be considered in all respects as illustrative and not restrictive, and all changes that come within the meaning and range of equivalency of the claims are intended to be embraced within their scope. [Explanation of symbols]

[0076] 15 Systems 20. Turbine Engine 21 Fan 22 Compressor 25 Combustor 30 Transmission 31 Drive mechanism (HP) 32 Drive mechanism (LP) 33 Transmission 34 Power Transmission (PT) Clutch 40 Bleed Air System 41 First Port 42 Second Port 43 Passage 44 Passage 45 valves 46 Passage 47 Passage 48 Precooler Aisle 49 50 Open differential gear set 51 One-way differential gear set 55 Housing 60 Accessories 70 First Compressor (LP) 71 First Axis 72 Turbine (LP) 75 spool (LP) 80 Second Compressor (HP) 81 Second Axis 82 Turbine (HP) 85 spool (HP) 90 Gearbox 100 aircraft 102 Cockpit 103 Torso 110 Aircraft Systems 120 Controller 121 Processing circuit 122 Memory Circuit 123 Communication Circuit 124 User Interface 125 input devices 126 Display 129 Programming Instructions

Claims

1. 1. A system (15) configured to be operatively connected to a turbine engine (20) of an aircraft (100) and an accessory (60) of the aircraft (100), comprising: A system (15) configured to selectively transfer power between a first pressure spool (75) of the turbine engine (20) and a second pressure spool (85) of the turbine engine (20) to power the accessory (60).

2. The system (15) of claim 1, wherein the system (15) comprises a transmission (30) having a gearbox (33) and a clutch (32).

3. the transmission (30) is configured to selectively operate in one of a first configuration, a second configuration, and a third configuration; the first arrangement transmits power from the turbine engine to the accessory; the second arrangement transmits power from the first pressure spool (75) to the second pressure spool (85); 3. The system (15) of claim 2, wherein the third configuration prevents the transmission of power from the turbine engine (20) to the accessory (60) and prevents the transmission of power from the first pressure spool (75) to the second pressure spool (85).

4. 4. The system (15) of claim 3, wherein in the first configuration, the transmission (33) is powered by the second pressure spool (85).

5. Transmission (30), a first drive mechanism (31) connecting the first pressure spool (75) to the transmission (30); and The system (15) of claim 1, further comprising a second drive mechanism (32) connecting the second pressure spool (85) to the transmission (30).

6. 2. The system of claim 1, wherein the accessory is a compressor, and the system further comprises a transmission configured to operate at different speeds to cause the compressor to supply air at a desired pressure to an aircraft system of the aircraft.

7. 2. The system (15) of claim 1, further comprising a controller (120) having a processing circuit (121), the controller (120) configured to drive the accessory and transfer the power generated from the first pressure spool (75) to the second pressure spool (85).

8. The system (15) of claim 7, wherein the controller (120) is integrated within the body of the transmission (30).

9. The system of claim 7 , wherein the controller is further configured to operate one or more components of an aircraft system of the aircraft.

10. 2. The system (15) of claim 1, further comprising a transmission (30), the transmission (30) configured to transfer power from the first pressure spool (75) to the second pressure spool (85) and to transfer power from the second pressure spool (85) to the first pressure spool (75).

11. 3. The system (15) of claim 2, wherein the transmission (33) is powered by the first pressure spool (75).

12. 2. The system of claim 1, wherein the accessory is a compressor, the first pressure spool is a low pressure spool, and the second pressure spool is a high pressure spool, and the system is configured to selectively transfer power between the low pressure spool and the high pressure spool to supply air to an aircraft system of the aircraft.

13. A system (15) configured to be operatively connected to a turbine engine (20) of an aircraft (100), comprising: Accessories (60), Transmission (30), a first drive mechanism (31) connecting the transmission (30) to a second pressure spool (85) of the turbine engine (20); and a second drive mechanism (32) connecting the transmission (30) to a first pressure spool (75) of the turbine engine (20); the transmission (30) is configured to transmit power of the turbine engine (20) via the first drive mechanism (31) and the second drive mechanism (32); The system (15), wherein the transmission (30) is configured to drive the accessory (60).

14. 14. The system (15) of claim 13, wherein the transmission (30) is configured to transmit the power from the first pressure spool (75) to the second pressure spool (85) via the first drive mechanism (31) and the second drive mechanism (32).

15. 14. The system (15) of claim 13, wherein the transmission (30) is configured to transmit the power from the second pressure spool (85) to the first pressure spool (75) via the first drive mechanism (31) and the second drive mechanism (32).

16. 14. The system (15) of claim 13, wherein the transmission (30) comprises a gearbox (33) operatively connected to and powered by the second pressure spool (85), and a clutch (36).

17. 17. The system (15) of claim 16, wherein the transmission (33) is a continuously variable transmission.

18. 14. The system (15) of claim 13, wherein the transmission (30) comprises a gearbox (33) operatively connected to and powered by the first pressure spool (75).

19. 14. The system of claim 13, further comprising a bleed air system comprising one or more ports and a first passageway through which air is supplied from the turbine engine to the aircraft.

20. 20. The system of claim 19, wherein the accessory is a compressor, and the bleed air system further comprises a second passageway separate from the first passageway for supplying air from the turbine engine to the compressor.

21. 14. The system of claim 13, further comprising a controller configured to selectively operate the transmission in a first mode for transmitting the power of the turbine engine via the first drive mechanism and the second drive mechanism, and in a second mode for driving the accessory.

22. 22. The system of claim 21, wherein the controller is further configured to control operation of a bleed air system that supplies air from the turbine engine to the aircraft.

23. The system (15) of claim 13, further comprising a bleed air system (40) configured to supply air from the turbine engine (20) to the accessory (60).

24. 1. A method of transmitting mechanical power in a turbine engine of an aircraft (100), comprising: placing a transmission (30) in a first configuration to transmit power from the turbine engine (20) to an accessory (60); and placing the transmission (30) in a second configuration and transmitting power from a first pressure spool (75) of the turbine engine (20) to a second pressure spool (85) of the turbine engine (20).

25. 25. The method of claim 24, wherein the accessory is a compressor, and further comprising transferring power from the turbine engine to the compressor and supplying air from the turbine engine to an aircraft system.

26. 25. The method of claim 24, wherein the first pressure spool is a low pressure spool and the second pressure spool is a high pressure spool, and placing the transmission in the second configuration comprises transferring power from the low pressure spool of the turbine engine to the high pressure spool of the turbine engine.

27. 26. The method of claim 25, further comprising providing air to the aircraft system (110) via a bleed air system (40) when the transmission (30) is in the first configuration.

28. The method of claim 25, further comprising preventing power from being transferred from the turbine engine (20) to the accessory (60) in the second configuration.

29. 26. The method of claim 25, wherein the second pressure spool is a high-pressure spool, and the method further comprises transmitting the power from the high-pressure spool of the turbine engine to the accessory in the first configuration.

30. 27. The method of claim 26, further comprising placing the transmission (30) in a third configuration to transfer power from the high pressure spool (85) to the low pressure spool (75).

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