Aircraft, aircraft bleed air system, and method for providing thrust to an aircraft

Abstract

An aircraft, an aircraft bleed air system, and a method of providing thrust for an aircraft. The bleed air system includes a bleed air turbine configured to receive at least a first portion of bleed air from a jet engine and to deliver the at least first portion of bleed air to a cabin, a cabin bleed air compressor operably coupled to the bleed air turbine and configured to receive cabin bleed air from the cabin, and a cabin bleed air nozzle configured to receive cabin bleed air from the cabin bleed air compressor. The aircraft includes a fuselage, a wing, a jet engine, and the bleed air system. The method includes the steps of expanding at least a first portion of bleed air from a jet engine to drive a cabin bleed air compressor, compressing cabin bleed air from a cabin with the cabin bleed air compressor, and ejecting the cabin bleed air into an environment.

Description

Technical Field

[0001] This disclosure relates to the bleed air system of an aircraft. Background Technology

[0002] In modern jet aircraft, a portion of the air compressed in the jet engine's compressor is typically transferred to various aerodynamic systems. However, this "bleed air" degrades the jet engine's performance. Furthermore, the bleed air pressure must typically be reduced, and in some cases significantly reduced, to be usable in downstream aerodynamic systems. This pressure reduction results in unused or incomplete heat utilization, leading to wasted electricity and consequently reducing the overall efficiency of the aircraft. Summary of the Invention

[0003] The bleed air system includes a bleed air turbine, a nacelle exhaust compressor, and nacelle exhaust nozzles. The bleed air turbine is configured to receive at least a first portion of bleed air from the aircraft's jet engines and deliver that first portion of bleed air to the aircraft's nacelle. The nacelle exhaust compressor is operatively coupled to the bleed air turbine and configured to receive nacelle exhaust from the nacelle. The nacelle exhaust nozzles are configured to receive nacelle exhaust from the nacelle exhaust compressor, thereby providing thrust to the aircraft.

[0004] According to this disclosure, the aircraft includes a fuselage, wings supported by the fuselage, a jet engine supported by the wings, and an air bleed system.

[0005] A method for providing thrust to an aircraft includes the following steps: expanding at least a first portion of bleed air from a jet engine of the aircraft to drive a cabin exhaust compressor; compressing cabin exhaust from the cabin of the aircraft with the cabin exhaust compressor; and injecting the cabin exhaust into the environment.

[0006] Clause 1. An air bleed system (10) for an aircraft (12) having a jet engine (16) and a cabin (18), said air bleed system (10) comprising: Bleed air turbine (20), which is configured to receive at least a first portion (22') of bleed air (22) from the jet engine (16) and deliver the at least first portion (22') of bleed air (22) to the cabin (18). A nacelle exhaust compressor (24), operably coupled to the bleed air turbine (20) and configured to receive nacelle exhaust (26) from the nacelle (18); and A cabin exhaust nozzle (28) is configured to receive cabin exhaust (26) from the cabin exhaust compressor (24) to provide thrust to the aircraft (12).

[0007] Clause 2. The bleed air system (10) according to Clause 1, the bleed air system further includes a bleed air ambient air heat exchanger (30), which is configured to: The at least first portion (22') of the bleed air (22) received from the jet engine (16); Ambient air (32) is received from the environment (34) via ambient air inlet (36); Cooling the at least first portion (22') of the bleed air (22); and The first portion (22') of the bleed air (22) is delivered to the cabin exhaust compressor (24).

[0008] Clause 3. The air elicitation system (10) according to Clause 2 further comprises: An ambient air fan (38), operatively coupled to the cabin exhaust compressor (24) and configured to receive ambient air (32) from the bleed air ambient air heat exchanger (30); and An ambient air nozzle (40) is configured to receive ambient air (32) from the ambient air fan (38) to provide thrust to the aircraft (12).

[0009] Clause 4. The bleed air system (10) according to Clause 1 further includes a bleed air water extractor (42) configured to receive at least a first portion (22') of the bleed air (22) from the bleed air turbine (20) and extract bleed air water (44) from the at least first portion (22') of the bleed air (22).

[0010] Clause 5. The air eliminator system (10) according to Clause 4 further comprises: Bleed air ambient air heat exchanger (30), which is configured as follows: The at least first portion (22') of the bleed air (22) received from the jet engine (16); Ambient air (32) is received from the environment (34) via ambient air inlet (36); Cooling the at least first portion (22') of the bleed air (22); and The first portion (22') of the bleed air (22) is delivered to the cabin exhaust compressor (24). The air-drawing water extractor (42) is configured to deliver the air-drawing water (44) to the ambient air (32) for delivering humid ambient air (32') to the air-drawing ambient air heat exchanger (30).

[0011] Clause 6. The bleed air system (10) according to Clause 1, the bleed air system further includes a bleed air splitter (46) configured to: The air intake (22) is divided into the first part (22') and the second part (22''); The first portion (22') is fed to the bleed air turbine (20); and The second part (22'') is delivered to the cabin (18).

[0012] Clause 7. The bleed air system (10) according to Clause 1, the bleed air system further includes a bleed air cooler (48) configured to: The jet engine (16) receives the bleed air (22); Receive cooling air (50); and Cool the bleed air (22).

[0013] Clause 8. The bleed air system (10) as described in Clause 7, wherein the cooling air (50) is bypass air from the engine fan of the jet engine (16).

[0014] Clause 9. The bleed air system (10) according to Clause 1, the bleed air system further includes a bleed air pressure regulating shut-off valve (54) located upstream of the bleed air turbine (20) and configured to: The jet engine (16) receives the bleed air (22); Adjust the pressure of the bleed air (22); and The bleed air is selectively cut off in response to the input (22).

[0015] Clause 10. The bleed air system (10) according to Clause 1, the bleed air system further includes a bleed air high-pressure shut-off valve (56), which is located upstream of the bleed air turbine (20) and configured to: Receive the bleed air (22) from the jet engine (16); and The air intake (22) is allowed to flow only when the pressure of the air intake (22) exceeds the threshold pressure.

[0016] Clause 11. The bleed air system (10) according to Clause 1, wherein the bleed air system (10) is configured to receive the bleed air (22) from the high-pressure compressor stage (58) of the jet engine (16).

[0017] Clause 12. An aircraft (12) comprising: Fuselage (60); Wing (62), which is supported by the fuselage (60); A jet engine (16), which is supported by the wing (62); and According to Clause 1, the air intake system (10) is as described.

[0018] Clause 13. The aircraft (12) according to Clause 12, wherein the bleed air turbine (20) and the cabin exhaust compressor (24) are supported by the wing (62).

[0019] Clause 14. A method (100) for providing thrust to an aircraft (12), the method (100) comprising the steps of: At least a first portion (22') of the bleed air (22) from the jet engine (16) of the aircraft (12) is expanded to drive the cabin exhaust compressor (24) (102). The cabin exhaust (26) (104) from the cabin (18) of the aircraft (12) is compressed by the cabin exhaust compressor (24); and The nacelle exhaust (26) is sprayed into the environment (34) (106).

[0020] Clause 15. The method (100) according to Clause 14, the method further comprising cooling at least the first portion (22') of the bleed air (22) upstream of the expansion (102) step (108).

[0021] Clause 16. The method (100) according to Clause 15, the method further comprising pre-cooling the at least first portion (22') of the bleed air (22) upstream of the cooling (108) step (110).

[0022] Clause 17. The method (100) according to Clause 15, the method further comprising reducing the pressure (112) of the at least first portion (22') of the bleed air (22) upstream of the cooling (108) step.

[0023] Clause 18. The method (100) according to Clause 14, said method (100) further includes the following steps: The air intake (22) is divided into the first portion (22') and the second portion (22'') (114); and The second part (22'') is delivered to the cabin (18) (116).

[0024] Clause 19. The method (100) according to Clause 14, the method further comprising extracting air-inducing water (44) (118) from the at least first portion (22') of the air-inducing (22) downstream of the expansion (102) step.

[0025] Clause 20. The method (100) according to Clause 19, the method further comprising cooling at least a first portion (22') (108) of the priming air (22) upstream of the expansion (102) step, wherein the cooling (108) step is performed at least in part with the priming air water (44). Attached Figure Description

[0026] Figure 1 The illustration is based on the example aircraft of this disclosure.

[0027] Figure 2 This is a schematic diagram illustrating the aircraft and bleed air system according to this disclosure.

[0028] Figure 3 This is a flowchart schematically illustrating the method according to this disclosure. Detailed Implementation

[0029] Figure 1 A non-exclusive example of an aircraft 12 according to this disclosure is shown, which may include one or more bleed air systems 10. Although shown as a fixed-wing passenger aircraft comprising a fuselage 60 having a cabin 18, two wings 62 supported by the fuselage 60, and a jet engine 16 supported by each wing 62, other configurations of the aircraft 12 are also within the scope of this disclosure, including, for example, gyroplanes, military aircraft, autonomous aircraft, etc. Figure 1 One or more components of the bleed air system 10, as well as all optional components, are schematically shown, which may be supported or housed in one or more of the fuselage 60 and / or wings 62 of the aircraft 12.

[0030] Figure 2 The air intake system 10 according to this disclosure is schematically illustrated. Typically, in... Figure 2 In this disclosure, elements that may be included in a given example are shown with solid lines, while elements that are optional in a given example or correspond to a particular example are shown with dashed lines. However, elements indicated by solid lines are not required for all examples of this disclosure, and elements shown by solid lines may be omitted from a particular example without departing from the scope of this disclosure.

[0031] like Figure 2 As schematically shown, the bleed air system 10 includes at least a bleed air turbine 20, a cabin exhaust compressor 24, and a cabin exhaust nozzle 28. The bleed air turbine 20 is configured to receive at least a first portion 22' of the bleed air 22 from the jet engine 16 of the aircraft 12 and ultimately deliver this first portion of bleed air to the cabin 18 of the aircraft 12. The cabin 18 can be any volume of air that needs to be maintained under desired conditions, such as any volume of air within a desired pressure and humidity range. Typically, the cabin 18 of the aircraft 12 is the space where passengers and aircraft crew reside; however, the cabin 18 of the aircraft 12 with the bleed air system 10 can be any volume of conditioned air and is not limited to the passenger cabin of a passenger aircraft such as a scheduled flight.

[0032] exist Figure 2 In this design, jet engine 16 is schematically represented as a turbofan jet engine, which includes a fan 64, a compressor 66 having a low-pressure compressor stage 68 and a high-pressure compressor stage 58, a combustion chamber 70, a turbine 74 having a high-pressure turbine stage 76 and a low-pressure turbine stage 78, a shaft 72 operatively connecting the turbine 74 to the compressor 66, and a nozzle 80. Some bleed air systems 10 are configured to receive bleed air 22 from the high-pressure compressor stage 58 of jet engine 16. However, bleed air systems 10 can receive bleed air 22 from any suitable source or location of jet engine 16. Furthermore, bleed air systems 10 can be used with other configurations of jet engine 16, and jet engine 16 is not limited to turbofan jet engines.

[0033] like Figure 2 As schematically shown, a nacelle exhaust compressor 24 (e.g., via shaft 25) is operatively coupled to a bleed air turbine 20 and configured to receive nacelle exhaust 26 from the nacelle 18. Nacelle exhaust 26 is air extracted from or otherwise permitted to escape from the nacelle 18.

[0034] The nacelle exhaust nozzle 28 is configured to receive nacelle exhaust 26 from the nacelle exhaust compressor 24, thereby providing thrust to the aircraft 12. That is, the nacelle exhaust nozzle 28 is operably configured to eject nacelle exhaust 26 from the aircraft 12 to increase the forward thrust of the aircraft 12.

[0035] like Figure 2As schematically shown, some examples of the bleed air system 10 also include a bleed air ambient air heat exchanger 30, which is configured to receive at least a first portion 22' of bleed air 22 from the jet engine 16, receive ambient air 32 from the environment 34 through the ambient air inlet 36, cool at least a first portion 22' of bleed air 22, and deliver at least a first portion 22' of bleed air 22 to the bleed air turbine 20. In other words, the bleed air ambient air heat exchanger 30 uses ambient air to cool at least a first portion 22' of bleed air, not by mixing the two together, but by exchanging heat between the two airflows passing through the bleed air ambient air heat exchanger 30.

[0036] Some examples of such bleed air systems 10, including the bleed air ambient air heat exchanger 30, also include an ambient air fan 38 and an ambient air nozzle 40. When present, the ambient air fan 38 (e.g., via shaft 25) is operatively coupled to the nacelle exhaust compressor 24 and configured to receive ambient air 32 from the bleed air ambient air heat exchanger 30. That is, the ambient air fan 38 is driven by the bleed air turbine 20, as is the nacelle exhaust compressor 24. The ambient air nozzle 40 is configured to receive ambient air 32 from the ambient air fan 38, thereby providing thrust to the aircraft 12. That is, the ambient air nozzle 40 is operatively configured to expel ambient air 32 from the aircraft 12 to increase the forward thrust to the aircraft 12.

[0037] Continue to refer to Figure 2 Some bleed air systems 10 also include a bleed air water extractor 42, which is configured to receive at least a first portion 22' of bleed air 22 from the bleed air turbine 20 and extract bleed air water 44 therefrom. Specifically, the moisture content of the bleed air 22 may be greater than that required for delivery to the cabin 18. In some such examples that also include a bleed air ambient air heat exchanger 30, the bleed air water extractor 42 is configured to deliver bleed air water 44 to ambient air 32 for delivering humid ambient air 32' to the bleed air ambient air heat exchanger 30. In particular, the bleed air water 44 will be used to cool the ambient air 32 for more efficient cooling operation of the bleed air ambient air heat exchanger 30.

[0038] like Figure 2As schematically shown, some bleed air systems 10 also include a bleed air splitter 46 configured to divide bleed air 22 into a first portion 22' and a second portion 22'', delivering the first portion 22' to the bleed air turbine 20 as described above, and ultimately delivering the second portion 22'' to the nacelle 18. The second portion 22'' is typically a small fraction of the bleed air 22 (e.g., less than 10%, less than 5%, or less than 1% by volume) and is used to control the temperature of the air delivered to the nacelle 18. The second portion 22'' of the bleed air 22 may also be referred to or described as trimmed air. The bleed air system 10 will typically also include a mixing manifold 82 that receives the first portion 22' and the second portion 22'' of the bleed air 22, as well as optional ambient air, for operatively mixing the airflow under desired conditions for delivery to the nacelle 18.

[0039] Continue to refer to Figure 2 Some bleed air systems 10 also include a bleed air cooler 48 configured to receive bleed air 22 from the jet engine 16, receive cooling air 50, and cool the bleed air 22 before delivering it to the bleed air turbine 20. Additionally or alternatively, the bleed air cooler 48 may be described as or referred to as a heat exchanger. In examples of bleed air systems 10 that also include a bleed air ambient air heat exchanger 30, the bleed air cooler 48 may be described as a precooler. In some examples, the cooling air 50 is bypass air from the engine fan of the jet engine 16, i.e., air drawn in from the fan 64 of the turbofan jet engine; however, the cooling air 50 may be drawn in from any suitable source. In some examples of bleed air systems 10 that also include a bleed air splitter 46, the bleed air cooler 48 is located upstream of the bleed air splitter 46, such as... Figure 2 The diagram is schematically illustrated. In this document, "upstream" and "downstream" refer to the flow direction of the corresponding fluid. Thus, the first structure, described as being upstream of the second structure, receives the corresponding fluid before the second structure, and the second structure can be described as being downstream of the first structure relative to the fluid.

[0040] like Figure 2 As schematically shown, some bleed air systems 10 also include a bleed air flow control valve 52 located upstream of the bleed air turbine 20 and configured to receive bleed air 22 from the jet engine 16 and reduce the pressure of the bleed air 22. In an example of a bleed air system 10 that also includes a bleed air splitter 46, the bleed air flow control valve 52 may be located upstream of the bleed air splitter and thus configured to deliver bleed air 22 to the bleed air splitter 46. In an example of a bleed air system 10 that also includes a bleed air cooler 48, the bleed air flow control valve 52 may be located downstream of the bleed air cooler and thus configured to receive bleed air 22 from the bleed air cooler 48.

[0041] Continue to refer to Figure 2 Some bleed air systems 10 also include a bleed air pressure regulating shut-off valve 54 located upstream of the bleed air turbine 20 and configured to receive bleed air 22 from the jet engine 16, regulate the pressure of the bleed air 22, and selectively shut off the bleed air 22 in response to an input. For example, the bleed air pressure regulating shut-off valve 54 may be configured to shut off the bleed air 22 in response to the detection of an engine fire. In some examples that also include a bleed air splitter 46, the bleed air pressure regulating shut-off valve 54 is located upstream of the bleed air splitter 46. In some examples that also include a bleed air cooler 48, the bleed air pressure regulating shut-off valve 54 may be located upstream of the bleed air cooler 48. In some examples that also include a bleed air flow control valve 52, the bleed air pressure regulating shut-off valve 54 is located upstream of the bleed air flow control valve 52.

[0042] For example Figure 2 As schematically shown, some bleed air systems 10 also include a high-pressure bleed air shut-off valve 56 located upstream of the bleed air turbine 20 and configured to receive bleed air 22 from the jet engine 16, allowing bleed air 22 to flow only when the pressure of bleed air 22 exceeds a threshold pressure. For example, the high-pressure bleed air shut-off valve 56 may be a check valve that opens only when the pressure of bleed air 22 is above the threshold pressure. In some examples that also include a bleed air splitter 46, the high-pressure bleed air shut-off valve 56 is located upstream of the bleed air splitter 46. In some examples that also include a bleed air cooler 48, the high-pressure bleed air shut-off valve 56 is located upstream of the bleed air cooler 48. In some examples that also include a bleed air flow control valve 52, the high-pressure bleed air shut-off valve 56 is located upstream of the bleed air flow control valve 52. In some examples that also include a bleed air pressure regulating shut-off valve 54, the high-pressure bleed air shut-off valve 56 is located upstream of the bleed air pressure regulating shut-off valve 54.

[0043] Figure 3 A flowchart is provided schematically to illustrate an illustrative, non-exclusive example of method 100 according to this disclosure. Figure 3 In the dashed boxes, some steps are shown, indicating that these steps may be optional or may correspond to specific examples of method 100 according to this disclosure. That is, not all methods 100 according to this disclosure need to include the steps shown in the solid boxes. Figure 3 The methods 100 and steps shown are not limiting, and other methods and steps are also within the scope of this disclosure, including methods 100 with a number of steps greater or less than those shown, as can be understood from the discussion herein.

[0044] like Figure 3 The diagram is shown schematically and with reference to Figure 2Method 100 typically includes the following steps: at least 102 expanding at least a first portion 22' of bleed air 22 from a jet engine 16 of the aircraft 12 to drive a cabin exhaust compressor 24; compressing 104 cabin exhaust 26 from the cabin 18 of the aircraft 12 with the cabin exhaust compressor 24; and injecting 106 of the cabin exhaust 26 into the environment 34. Therefore, method 100 can be described as a method of providing thrust to the aircraft 12. Additionally or alternatively, method 100 can be described as, or referred to as, a bleed air method. Although the elements of method 100 are... Figure 2 The reference numerals in the accompanying drawings are used to indicate the method 100, and the method 100 may be implemented by the air intake system 10 according to the present disclosure, but the method 100 is not limited to being implemented by the air intake system 100.

[0045] Some methods 100 further cool at least a first portion 22' of the bleed air 22 upstream of the expansion step 102. Some such methods 100 also include at least pre-cooling the first portion 22' of the bleed air 22 upstream of the cooling step 108.

[0046] Some methods 100 include reducing the pressure of at least a first portion 22' of the bleed air 22 upstream of the cooling step 108. In some such examples, the pre-cooling step 110 is performed upstream of the reduction step 112.

[0047] Some methods 100 also include: splitting the bleed air 22 114 into a first portion 22' and a second portion 22''; and finally delivering the second portion 22'' to the cabin 18 of the aircraft 12 by 116. In some such examples, the splitting step 114 is upstream of the cooling step 108. In some examples, the pre-cooling step 110 is upstream of the splitting step 114.

[0048] Some methods 100 also include extracting 118 bleed water 44 from at least a first portion 22' of the bleed air 22 downstream of the expansion step 102. In some such examples, the cooling step 108 is performed at least partially with the bleed water 44.

[0049] Some methods 100 also include combining bleed air 44 with ambient air 32 120 to generate humid ambient air 32'. In some such examples, the cooling step 108 is performed with humid ambient air 32'. Some methods 100 also include injecting (122) humid ambient air 32' into the environment 34 to provide additional thrust to the aircraft 12.

[0050] The following paragraphs describe illustrative, non-exclusive examples of the inventive subject matter according to this disclosure: A. A bleed air system (10) for an aircraft (12) having a jet engine (16) and a cabin (18), the bleed air system (10) comprising: Bleed air turbine (20), which is configured to receive at least a first portion (22') of bleed air (22) from the jet engine (16) and deliver at least a first portion (22') of the bleed air (22) to the nacelle (18). A nacelle exhaust compressor (24), operably coupled to the bleed air turbine (20) and configured to receive nacelle exhaust (26) from the nacelle (18); and A cabin exhaust nozzle (28) is configured to receive cabin exhaust (26) from the cabin exhaust compressor (24) to provide thrust to the aircraft (12).

[0051] A1. According to the bleed air system (10) described in paragraph A, the bleed air system further includes a bleed air ambient air heat exchanger (30), which is configured as follows: Receive at least a first portion (22') of the bleed air (22) from the jet engine (16); Ambient air (32) is received from the environment (34) via ambient air inlet (36); Cool at least the first portion (22') of the bleed air (22); and At least a first portion (22') of the bleed air (22) is delivered to the cabin exhaust compressor (24).

[0052] A1.1. According to the air intake system (10) described in paragraph A1, the air intake system further includes: An ambient air fan (38), operatively coupled to the cabin exhaust compressor (24) and configured to receive ambient air (32) from the bleed air ambient air heat exchanger (30); and An ambient air nozzle (40) is configured to receive ambient air (32) from the ambient air fan (38) to provide thrust to the aircraft (12).

[0053] A2. The bleed air system (10) according to any of paragraphs A to A1.1, the bleed air system further includes a bleed air water extractor (42) configured to receive at least a first portion (22') of the bleed air (22) from the bleed air turbine (20) and extract bleed air water (44) from the at least first portion (22') of the bleed air (22).

[0054] A2.1. The induced draft system (10) according to paragraph A2 of paragraph A1, wherein the induced draft water extractor (42) is configured to deliver the induced draft water (44) to the ambient air (32) for delivering humid ambient air (32') to the induced draft ambient air heat exchanger (30).

[0055] A3. The bleed air system (10) according to any of paragraphs A to A2.1, the bleed air system further includes a bleed air splitter (46) configured to: The air intake (22) is divided into a first part (22') and a second part (22''). The first portion (22') is delivered to the bleed air turbine (20); and The second part (22'') is delivered to the cabin (18).

[0056] A4. The bleed air system (10) described in any of paragraphs A through A3, the bleed air system further comprising a bleed air cooler (48) configured to: The jet engine (16) receives the bleed air (22); Receive cooling air (50); and Cool the bleed air (22).

[0057] A4.1. According to paragraph A4, the bleed air system (10) wherein the cooling air (50) is bypass air from the engine fan of the jet engine (16).

[0058] A4.2. The bleed air system (10) according to any one of paragraphs A4 to A4.1 of paragraph A3, wherein the bleed air cooler (48) is located upstream of the bleed air splitter (46).

[0059] A5. The bleed air system (10) described in any of paragraphs A through A4.2 further includes a bleed air flow control valve (52) located upstream of the bleed air turbine (20) and configured to: The jet engine (16) receives the bleed air (22); and Reduce the pressure of the bleed air (22).

[0060] A5.1. The bleed air system (10) according to paragraph A5 of paragraph A3, wherein the bleed air flow control valve (52) is configured to deliver the bleed air (22) to the bleed air distributor (46).

[0061] A5.2. According to the bleed air system (10) described in paragraph A5.1 of paragraph A4, wherein the bleed air flow control valve (52) is configured to receive the bleed air (22) from the bleed air cooler (48).

[0062] A6. The bleed air system (10) according to any of paragraphs A through A5.2, the bleed air system further includes a bleed air pressure regulating shut-off valve (54) located upstream of the bleed air turbine (20) and configured to: The jet engine (16) receives the bleed air (22); Adjust the pressure of the bleed air (22); and The bleed air is selectively cut off in response to the input (22).

[0063] A6.1. The bleed air system (10) according to paragraph A6 of paragraph A3, wherein the bleed air pressure regulating shut-off valve (54) is located upstream of the bleed air splitter (46).

[0064] A6.2. The bleed air system (10) according to any one of paragraphs A6 to A6.1 of paragraph A4, wherein the bleed air pressure regulating shut-off valve (54) is located upstream of the bleed air cooler (48).

[0065] A6.3. The bleed air system (10) according to any one of paragraphs A6 to A6.2 of paragraph A5, wherein the bleed air pressure regulating shut-off valve (54) is located upstream of the bleed air flow control valve (52).

[0066] A7. The bleed air system (10) described in any of paragraphs A through A6.3 further includes a high-pressure bleed air shut-off valve (56) located upstream of the bleed air turbine (20) and configured to: The jet engine (16) receives the bleed air (22); and The air intake (22) is allowed to flow only when the pressure of the air intake (22) exceeds the threshold pressure.

[0067] A7.1. According to the bleed air system (10) described in paragraph A7 of paragraph A3, wherein the bleed air high pressure shut-off valve (56) is located upstream of the bleed air distributor (46).

[0068] A7.2. The bleed air system (10) according to any one of paragraphs A7 to A7.1 of paragraph A4, wherein the bleed air high pressure shut-off valve (56) is located upstream of the bleed air cooler (48).

[0069] A7.3. The bleed air system (10) according to any one of paragraphs A7 to A7.2 of paragraph A5, wherein the bleed air high pressure shut-off valve (56) is located upstream of the bleed air flow control valve (52).

[0070] A7.4. The bleed air system (10) according to any one of paragraphs A7 to A7.3 of paragraph A6, wherein the bleed air high pressure shut-off valve (56) is located upstream of the bleed air pressure regulating shut-off valve (54).

[0071] A8. The bleed air system (10) according to any of paragraphs A to A7.4, wherein the bleed air system (10) is configured to receive bleed air (22) from the high-pressure compressor stage (58) of the jet engine (16).

[0072] B. An aircraft (12), said aircraft comprising: Fuselage (60); Wing (62), which is supported by the fuselage (60); A jet engine (16), which is supported by the wing (62); and The air intake system (10) described in any of paragraphs A through A8.

[0073] B1. The aircraft (12) according to paragraph B, wherein the bleed air turbine (20) and the cabin exhaust compressor (24) are supported by the wing (62).

[0074] B2. The aircraft (12) described in any of paragraphs B to B1, wherein the bleed air turbine (20) and the cabin exhaust compressor (24) are housed within the wing (62).

[0075] B3. The aircraft (12) described in any of paragraphs B to B2 of paragraph A1.1, wherein the ambient air fan (38) is supported by the wing (62).

[0076] B4. The aircraft (12) described in any of paragraphs B to B3 of paragraph A1.1, wherein the ambient air fan (38) is housed within the wing (62).

[0077] C. A method (100) for providing thrust to an aircraft (12), the method (100) comprising the steps of: The expansion (102) is generated from at least the first portion (22') of the bleed air (22) of the jet engine (16) of the aircraft (12) to drive the cabin exhaust compressor (24). The cabin exhaust (26) from the cabin (18) of the aircraft (12) is compressed (104) by the cabin exhaust compressor (24); and The nacelle exhaust (26) is sprayed (106) into the environment (34).

[0078] C1. According to the method (100) in paragraph C, the method further includes cooling (108) at least a first portion (22') of the bleed air (22) upstream of the expansion step (102).

[0079] C1.1. The method (100) according to paragraph C1 further includes pre-cooling (110) at least a first portion (22') of the bleed air (22) upstream of the cooling step (108).

[0080] C1.2. The method (100) according to any of paragraphs C1 to C1.1, the method further comprising reducing (112) the pressure of at least a first portion (22') of the bleed air (22) upstream of the cooling step (108).

[0081] C1.2.1. The method (100) according to paragraph C1.2 of paragraph C1.1, wherein the precooling step (110) is performed upstream of the lowering step (112).

[0082] C2. The method (100) according to any of paragraphs C to C1.2.1, the method further comprising the following steps: The air intake (22) is split (114) into a first part (22') and a second part (22''); and The second part (22'') is delivered (116) to the cabin (18).

[0083] C2.1. The method (100) according to paragraph C2 of paragraph C1, wherein the diversion step (114) is located upstream of the cooling step (108).

[0084] C2.2. The method (100) according to any one of paragraphs C2 to C2.1 of paragraph C1.1, wherein the precooling step (110) is located upstream of the diversion step (114).

[0085] C3. The method (100) according to any of paragraphs C to C2.2, the method further comprising extracting (118) air-intake water (44) from at least a first portion (22') of the air-intake (22) downstream of the expansion step (102).

[0086] C3.1. The method (100) according to paragraph C3 of paragraph C1, wherein the cooling step (108) is performed at least in part with the priming water (44).

[0087] C3.2. The method (100) according to any of paragraphs C3 to C3.1, the method further comprising (120) combining the priming water (44) with ambient air (32) to generate humid ambient air (32').

[0088] C3.2.1. The method according to paragraph C3.2, wherein the cooling step (108) is performed using the humid ambient air (32').

[0089] C3.2.2. The method (100) according to any of paragraphs C3.2 to C3.2.1, the method further comprising spraying (122) the humid ambient air (32') into the environment (34).

[0090] C4. The method (100) according to any of paragraphs C to C3.2.2, wherein the method (100) is performed using the air intake system (10) according to any of paragraphs A to A8.

[0091] D. Use the air intake system (10) described in any of paragraphs A through A8 to provide thrust to the aircraft (12).

[0092] As used herein, the terms “adjustment” and “configuration” mean that an element, component, or other subject is designed and / or intended to perform a given function. Therefore, the use of the terms “adjustment” and “configuration” should not be construed as meaning that a given element, component, or other subject is merely “capable” of performing a given function, but rather that the element, component, and / or other subject is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing that function. Also within the scope of this disclosure, elements, components, and / or other stated subjects that are said to be suitable for performing a particular function may additionally or alternatively be described as being configured to perform that function, and vice versa. Similarly, subjects that are said to be configured to perform a particular function may additionally or alternatively be described as being operable to perform that function.

[0093] As used herein, the term “and / or” between the first entity and the second entity refers to one of (1) the first entity, (2) the second entity, and (3) the first entity and the second entity. Multiple entities listed with “and / or” shall be interpreted in the same manner, i.e., entities connected as “one or more”. Other entities may optionally appear, whether related to or unrelated to the specifically designated entities, in addition to those specifically indicated by the “and / or” clause. Thus, as a non-restrictive example, when used in conjunction with open-ended language such as “includes”, a reference to “A and / or B” may in one example refer only to A (optionally including entities other than B); in another example, only to B (optionally including entities other than A); and in yet another example, to both A and B (optionally including other entities). These entities may refer to elements, actions, structures, steps, operations, values, etc.

[0094] The various disclosed elements and method steps of the apparatus disclosed herein are not essential to all apparatuses and methods according to this disclosure, which includes all novel and non-obvious combinations and sub-combinations of the various elements and steps disclosed herein. Furthermore, one or more of the various elements and steps disclosed herein may define an independent inventive subject matter separate from the overall disclosed apparatus or method. Therefore, such inventive subject matter does not need to be associated with the specific apparatus and method explicitly disclosed herein, and such inventive subject matter may find utility in apparatuses and / or methods not explicitly disclosed herein.

Claims

1. A bleed air system (10) for an aircraft (12) having a jet engine (16) and a cabin (18), the bleed air system (10) comprising: Bleed air turbine (20), which is configured to receive at least a first portion (22') of bleed air (22) from the jet engine (16) and deliver the at least first portion (22') of bleed air (22) to the cabin (18). A nacelle exhaust compressor (24) is operatively coupled to the bleed air turbine (20) and configured to receive nacelle exhaust (26) from the nacelle (18). as well as A cabin exhaust nozzle (28) is configured to receive cabin exhaust (26) from the cabin exhaust compressor (24) to provide thrust to the aircraft (12).

2. The bleed air system (10) according to claim 1, further comprising a bleed air ambient air heat exchanger (30), the bleed air ambient air heat exchanger being configured as follows: The at least first portion (22') of the bleed air (22) received from the jet engine (16); Ambient air (32) is received from the environment (34) via ambient air inlet (36); Cooling the at least first portion (22') of the bleed air (22); and The first portion (22') of the bleed air (22) is delivered to the cabin exhaust compressor (24).

3. The air eliminator system (10) according to claim 2, wherein the air eliminator system further comprises: An ambient air fan (38), operatively coupled to the cabin exhaust compressor (24) and configured to receive ambient air (32) from the bleed air ambient air heat exchanger (30); and An ambient air nozzle (40) is configured to receive ambient air (32) from the ambient air fan (38) to provide thrust to the aircraft (12).

4. The air intake system (10) according to claim 1, the air intake system further comprising an air intake water extractor (42) configured to receive at least a first portion (22') of the air intake (22) from the air intake turbine (20) and extract air intake water (44) from the at least first portion (22') of the air intake (22).

5. The air eliminator system (10) according to claim 4, wherein the air eliminator system further comprises: Bleed air ambient air heat exchanger (30), which is configured as follows: The at least first portion (22') of the bleed air (22) received from the jet engine (16); Ambient air (32) is received from the environment (34) via ambient air inlet (36); Cooling the at least first portion (22') of the bleed air (22); and The first portion (22') of the bleed air (22) is delivered to the cabin exhaust compressor (24). The air-drawing water extractor (42) is configured to deliver the air-drawing water (44) to the ambient air (32) for delivering humid ambient air (32') to the air-drawing ambient air heat exchanger (30).

6. The bleed air system (10) according to claim 1, further comprising a bleed air splitter (46) configured to: The air intake (22) is divided into the first part (22') and the second part (22''); The first portion (22') is fed to the bleed air turbine (20); and The second part (22'') is delivered to the cabin (18).

7. The bleed air system (10) according to claim 1, further comprising a bleed air cooler (48) configured to: The jet engine (16) receives the bleed air (22); Receive cooling air (50); and Cool the bleed air (22).

8. The air intake system (10) according to claim 7, wherein, The cooling air (50) is bypass air from the engine fan of the jet engine (16).

9. An aircraft (12), said aircraft comprising: Fuselage (60); Wing (62), which is supported by the fuselage (60); A jet engine (16) is supported by the wing (62); as well as The air intake system (10) according to claim 1.

10. A method (100) for providing thrust to an aircraft (12), the method (100) comprising the steps of: At least a first portion (22') of the bleed air (22) from the jet engine (16) of the aircraft (12) is expanded to drive the cabin exhaust compressor (24) (102). The cabin exhaust (26) (104) from the cabin (18) of the aircraft (12) is compressed by the cabin exhaust compressor (24); and The nacelle exhaust (26) is sprayed into the environment (34) (106).

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