Engine system and aircraft

Abstract

The application relates to the technical field of engines and discloses an engine system and an aircraft, the engine system comprising: an air generator; a bleed air pipeline in communication with the air generator; the bleed air pipeline extending inside the aircraft; a heat exchanger matched with part of a pipeline section of the bleed air pipeline; a turbofan engine internally provided with a gas collection chamber; the turbofan engine further comprising: an air inlet passage in communication with the bleed air pipeline at one end and in communication with the gas collection chamber at the other end; and a compressor in communication with the gas collection chamber; the engine system provided by the application realizes cooperation of compressed air of the air generator, cooling of airflow in the bleed air pipeline by the heat exchanger and secondary compression of air by the compressor, obtains an ultrahigh pressure ratio, reduces an oil consumption rate, has a larger space, i.e. an internal space of the aircraft, for designing the heat exchanger, and has a good practical application effect.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of engines, in particular to an engine system and an aircraft. BACKGROUND

[0002] A turbofan engine is a jet engine applied in the field of modern aviation, and its basic structure includes a fan, a compressor, a combustion chamber, a turbine, an outer duct and a nozzle; the turbine is divided into a high-pressure turbine and a low-pressure turbine, which extracts energy from high-temperature gas to drive the compressor and the fan.

[0003] In the industry, in order to further reduce the fuel consumption rate of the turbofan engine, the way of increasing the bypass ratio and / or the total pressure ratio of the compressor is usually adopted.

[0004] In the related art, the fuel consumption rate of the turbofan engine is often reduced by adding a reduction gear box or a heat exchanger in the turbofan engine; however, adding a reduction gear box between the fan and the low-pressure turbine can make the fan and the low-pressure turbine work at different speeds, thereby increasing the bypass ratio, but the introduction of the gear box increases the overall weight, and the lubrication and heat dissipation of the gear box are difficult, which limits its actual application; adding a heat exchanger between the high-pressure compressor and the low-pressure compressor can make the airflow of the fan outer duct and the airflow at the outlet of the low-pressure compressor exchange heat to reduce the total temperature of the airflow at the inlet of the high-pressure compressor, thereby further improving the design pressure ratio of the high-pressure compressor; however, due to the limited space inside the engine, the design of the heat exchanger faces problems such as small space and complex structure, which makes it difficult to implement in engineering. SUMMARY

[0005] Therefore, the present application provides an engine system and an aircraft to solve the problem that the turbofan engine with a reduction gear box or a heat exchanger has poor actual application effect or small heat exchange design space.

[0006] In a first aspect, the present application provides an engine system, comprising: an air generator adapted to introduce external air and compress; a bleed air pipeline in communication with the air generator; the bleed air pipeline is adapted to extend inside an aircraft; a heat exchanger is arranged in cooperation with part of the pipe section of the bleed air pipeline and is adapted to cool the compressed air; a turbofan engine having a gas collection chamber inside, the turbofan engine further comprising: an air inlet passage in communication with the bleed air pipeline at one end and in communication with the gas collection chamber at the other end, adapted to introduce the compressed air into the turbofan engine; a compressor in communication with the gas collection chamber, the compressor being adapted to compress the air twice.

[0007] In an alternative embodiment, the turbofan engine further comprises a baffle plate, a cover is arranged at the plenum chamber, the air inlet passage is arranged through the baffle plate; a fan is connected with the first shaft, the first shaft is adapted to drive the fan to rotate to introduce the bypass airflow; wherein the air inlet passage is adapted to introduce the core airflow, the core airflow is independent of the bypass airflow.

[0008] In an alternative embodiment, the bleed air pipeline is adapted to extend through the fuselage and the wing of the aircraft; the heat exchanger is arranged in the wing to cooperate with the pipeline segment of the bleed air pipeline arranged in the wing.

[0009] In an alternative embodiment, further comprising a hollow strut, the air inlet passage is arranged through the hollow strut; the hollow strut is arranged at the turbofan engine and arranged through the baffle plate; one end of the hollow strut is in communication with the bleed air pipeline, and the other end of the hollow strut is in communication with the plenum chamber.

[0010] In an alternative embodiment, the plenum chamber is arranged around the axis of the first shaft.

[0011] In an alternative embodiment, further comprising a combustion chamber, the combustion chamber is in communication with the compressor, the combustion chamber is adapted to mix and burn the air pressurized for the second time and the fuel.

[0012] In an alternative embodiment, further comprising a first turbine, the first turbine is in communication with the combustion chamber; a second turbine, the second turbine is arranged on the side of the first turbine away from the combustion chamber; a second shaft, the second shaft is arranged through the hole in the axial direction, the second shaft is sleeved on the peripheral portion of the first shaft and arranged in spaced relation with the first shaft; wherein the first turbine and the compressor are connected with the second shaft respectively; the second turbine is connected with the first shaft, the second turbine is adapted to drive the first shaft to rotate.

[0013] In an alternative embodiment, further comprising a first rear strut, the first rear strut is connected with the second shaft by means of a rotary member and arranged beside the fan.

[0014] In an alternative embodiment, further comprising a second rear strut, the second rear strut is connected with the first shaft by means of a rotary member and arranged on the side of the second turbine away from the first turbine.

[0015] In a second aspect, the present application further provides an aircraft, comprising: the engine system according to any one of the above-mentioned embodiments; a fuselage, the air generator is arranged at the fuselage; a wing, the wing is connected with the fuselage, and the turbofan engine is arranged at the wing.

[0016] Beneficial effects: The air generator introduces the ambient environment air, and performs preliminary compression on the ambient environment air; the bleed air pipeline is a gas flow pipeline between the air generator and the turbofan engine, and is arranged in a bent and extended mode in the interior of the aircraft; the heat exchanger is installed in the interior of the aircraft, and cooperates with part of the pipeline section of the bleed air pipeline to transmit the heat of the airflow to the air, so that the temperature of the airflow reaching the turbofan engine is reduced, and the power requirement of the compressor is further reduced, and the interior of the aircraft has a larger heat exchanger accommodation space; the compressor performs secondary compression on the ambient environment air, and provides the engine system with an ultrahigh pressure ratio by means of the ultrahigh pressure air after the two times of compression, so that the purpose of reducing the fuel consumption rate of the engine is achieved.

[0017] Beneficial effects: By means of the air generator, the heat exchanger and the compressor, the ultrahigh pressure ratio is obtained, the fuel consumption rate is reduced, a larger space (the interior space of the aircraft) is provided for the design of the heat exchanger, the cooling effect of the compressed airflow is improved, the energy required for the compression of the compressor is reduced, and the fuel efficiency is improved; the overall weight of the turbofan engine is not changed in a large range by replacing the mode of increasing the reduction gear box, and the actual application effect is good, and the heat exchange design space is large.

[0018] Beneficial effects: The air generator provides the turbofan engine with an additional, stable and sufficient air source by means of external air supply.

[0019] Beneficial effects: The inner-duct airflow and the outer-duct airflow are independent and physically isolated, the airflow compressed by the fan does not affect the inner-duct compressed airflow, the flow path of the inner-duct compressed airflow is completely closed and isolated from the outer-duct airflow, the high-pressure characteristics of the inner-duct airflow are ensured not to be disturbed, the energy loss is reduced, and the thrust performance is improved.

[0020] Beneficial effects: The heat exchanger can also heat the front part of the wing of the aircraft, so that icing of the wing during flight is prevented. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the following description of the specific embodiments or the prior art will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0022] Fig. 1 It is a schematic diagram of the engine system of the present application;

[0023] Fig. 2 It is a schematic diagram of the turbofan engine of the present application;

[0024] Fig. 3 It is a schematic diagram of the outer-duct airflow and the inner-duct airflow of the present application;

[0025] Fig. 4 Figure 4 is a side view of the gas collection chamber of the present application.

[0026] Reference signs:

[0027] 1. air generator;

[0028] 2. bleed air line;

[0029] 3. heat exchanger;

[0030] 4. turbofan engine; 41. blocker; 42. gas collection chamber; 43. compressor; 44. first shaft; 45. combustion chamber; 46. first turbine; 47. second turbine; 48. second shaft; 49. second blocker;

[0031] 5. fan; 51. first blocker; 52. wing panel;

[0032] 6. hollow blocker; 61. air inlet passage;

[0033] 7. outer bypass flow;

[0034] 8. inner bypass flow;

[0035] 9. aircraft; 91. fuselage; 92. wing. DETAILED DESCRIPTION

[0036] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0037] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0038] In the description of the present application, it should be noted that unless specifically defined and limited otherwise, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0039] In addition, the technical features involved in the different embodiments of the application described below can be combined with each other as long as there is no conflict.

[0040] The embodiments of the present application are described below in conjunction with Figs. 1 to 4

[0041] According to the embodiments of the present application, in one aspect, an engine system is provided, comprising: an air generator 1 adapted to introduce external air and compress; a bleed air pipeline 2 in communication with the air generator 1; the bleed air pipeline 2 is adapted to extend inside an aircraft 9; a heat exchanger 3 is arranged in cooperation with a part of the pipeline section of the bleed air pipeline 2, and is adapted to cool the compressed air; a turbofan engine 4, which has a plenum chamber 42 inside, and further comprises: an air inlet passage 61, one end of which is in communication with the bleed air pipeline 2, and the other end of which is in communication with the plenum chamber 42, and is adapted to introduce the compressed air into the turbofan engine 4; and a compressor 43, which is in communication with the plenum chamber 42, and is adapted to compress the air twice.

[0042] Specifically, the air generator 1 introduces ambient air and preliminarily compresses it; the bleed air pipeline 2 is a gas flow pipeline between the air generator 1 and the turbofan engine 4, and is arranged to extend inside the aircraft 9; the heat exchanger 3 is installed inside the aircraft 9 and cooperates with a part of the pipeline section of the bleed air pipeline 2 to transfer heat from the airflow to the air, thereby reducing the temperature of the airflow reaching the turbofan engine 4, and further reducing the power requirement of the compressor 43; the aircraft 9 has a large heat exchanger 3 accommodation space inside; the compressor 43 compresses the ambient air twice, and the super-high pressure air after two compressions provides a super-high pressure ratio for the engine system, thereby achieving the purpose of reducing the fuel consumption of the engine.

[0043] ​The engine system provided by the embodiment, by cooperating the air generator 1 to compress air, the heat exchanger 3 to cool the airflow in the air bleed pipe 2, and the air compressor 43 to compress air again, the super-high pressure ratio is obtained, the oil consumption rate is reduced, the heat exchanger 3 has a larger space (the internal space of the aircraft 9) to design, the cooling effect of the compressed airflow is improved, and then the energy required by the air compressor 43 to compress is reduced, the fuel efficiency is improved; instead of increasing the reduction gear box, the overall weight of the turbofan engine 4 does not change much, the practical application effect is good, and the heat exchange design space is large.

[0044] In the embodiment, the air generator 1 provides an additional, stable, and sufficient air source for the turbofan engine 4 through external air supply.

[0045] Preferably, the air compressor 43 is a high-pressure air compressor.

[0046] In some embodiments, the turbofan engine 4 further comprises a baffle plate 41 arranged at the air collection chamber 42, and the air inlet passage 61 is arranged through the baffle plate 41; a fan 5 connected with a first shaft 44, the first shaft 44 is adapted to drive the fan 5 to rotate to introduce the outer bypass airflow 7; wherein the air inlet passage 61 is adapted to introduce the inner bypass airflow 8, and the inner bypass airflow 8 is independent of the outer bypass airflow 7.

[0047] It should be noted that at the turbofan engine 4, the airflow is divided into the inner bypass airflow 8 and the outer bypass airflow 7, which work together to generate thrust; the inner bypass airflow 8 refers to the airflow flowing through the engine core part such as the air compressor 43 and the combustion chamber 45, and the outer bypass airflow 7 flows through the outer bypass duct without passing through the engine core part.

[0048] Specifically, the inner bypass airflow 8 is generated by the air generator 1, enters the air collection chamber 42 through the air bleed pipe 2 and the air inlet passage 61 for rectification, and then enters the air compressor 43 for further compression; the outer bypass airflow 7 is generated by the fan 5, and the fan blade of the fan 5 rotates to suck in air, wherein the inner bypass airflow 8 is independent of and physically isolated from the outer bypass airflow 7, so as to avoid the influence of the airflow compressed by the fan 5 on the inner bypass compressed airflow; the flow path of the inner bypass compressed airflow is completely closed and isolated from the outer bypass airflow 7, so as to ensure that the high-pressure characteristics of the inner bypass airflow 8 are not disturbed, reduce energy loss, and improve thrust performance.

[0049] In some embodiments, the air bleed pipe 2 is adapted to be arranged to extend in the fuselage 91 and the wing 92 of the aircraft 9; and the heat exchanger 3 is arranged in the wing 92 to cooperate with the pipe section of the air bleed pipe 2 located in the wing 92.

[0050] Specifically, the air generator 1 is arranged at the body 91 of the aircraft 9, and the air generator 1 is capable of sucking air from the external environment and performing compression processing, at least two air bleed pipes 2 are respectively communicated with the air generator 1, and are respectively arranged at the body 91 and the wings 92 on both sides of the aircraft 9, at least two turbofan engines 4 are respectively arranged at the wings 92 on both sides of the aircraft 9, and are respectively communicated with the air bleed pipes 2, at least two heat exchangers 3 are respectively arranged at the wings 92 on both sides of the aircraft 9, and are respectively matched with the air bleed pipes 2, and the air bleed pipes 2 are arranged in a bent mode in the wings 92, so that the heat exchangers 3 are matched with more pipe sections of the air bleed pipes 2, and the cooling effect on the airflow is improved.

[0051] Preferably, the heat exchanger 3 can also heat the front section of the wing 92 of the aircraft 9, so as to prevent icing of the wing 92 in the flight process.

[0052] In some embodiments, further comprising a hollow support plate 6, and the air inlet passage 61 is arranged in the hollow support plate 6 in a penetrating mode; the hollow support plate 6 is arranged at the turbofan engine 4 and penetrates the baffle plate 41; one end of the hollow support plate 6 is communicated with the air bleed pipe 2, and the other end is communicated with the air collection chamber 42.

[0053] Specifically, the hollow support plate 6 is internally provided with a passage, i.e., an air inlet passage, one side of the hollow support plate 6 is communicated with the air bleed pipe 2, and the other side is communicated with the air collection chamber 42 after penetrating the baffle plate 41; the air collection chamber 42 is surrounded by a wall body, and the air collection chamber 42 is arranged in a surrounding mode around the axis of the first shaft 44, i.e., the air collection chamber 42 is arranged in a surrounding mode at the peripheral portion of the first shaft 44.

[0054] In some embodiments, further comprising a combustion chamber 45, which is communicated with the compressor 43, and the combustion chamber 45 is adapted to mix and burn the air after secondary pressurization and fuel; a first turbine 46, which is communicated with the combustion chamber 45; a second turbine 47, which is located on the side of the first turbine 46 away from the combustion chamber 45; a second shaft 48, which is provided with a hole in the axial direction, and the second shaft 48 is sleeved on the peripheral portion of the first shaft 44 and is arranged in a spaced mode with the first shaft 44; wherein the first turbine 46 and the compressor 43 are respectively connected with the second shaft 48; the second turbine 47 is connected with the first shaft 44, and the second turbine 47 is adapted to drive the first shaft 44 to rotate; a first rear support plate 51, which is connected with the second shaft 48 by means of a rotary member and is located on the side of the fan 5; and a second rear support plate 49, which is connected with the first shaft 44 by means of a rotary member and is located on the side of the second turbine 47 away from the first turbine 46.

[0055] It should be noted that the first turbine 46 is a high-pressure turbine, and the second turbine 47 is a low-pressure turbine; the rotating member can be a bearing, and the bearing is sleeved on the first shaft 44 or the second shaft 48, and the first rear support plate 51 and the second rear support plate 49 are connected with the bearing respectively.

[0056] Specifically, the inner air flow 8 enters the air collection chamber 42 through the air inlet passage 61 at the hollow support plate 6, is further compressed by the compressor 43, and then enters the combustion chamber 45 to mix and burn fuel, so as to generate high-temperature and high-pressure gas. The high-temperature and high-pressure gas impacts the high-pressure turbine, i.e., the first turbine 46, and the first turbine 46 drives the compressor 43 to rotate by means of the second shaft 48, while the temperature and pressure are reduced, and then the high-temperature and high-pressure gas impacts the low-pressure turbine, i.e., the second turbine 47, and the second turbine 47 drives the fan 5 to rotate by means of the first shaft 44, so as to do work on the outer air flow 7; the inner air flow 8 is mixed with fuel and burned, and after passing through the second rear support plate 49, the inner air flow 8 is sprayed out of the rear opening of the turbofan engine 4 to generate thrust; the outer air flow 7 is sprayed out of the fan 5, the hollow support plate 6 and the first rear support plate 51 to generate thrust.

[0057] Optionally, the first rear support plate 51 is connected with a wing plate 52 on a side away from the second shaft 48, the wing plate 52 is arranged around the periphery of the fan 5, and the hollow support plate 6 penetrates through the wing plate 52.

[0058] According to the embodiment of the present application, on the other hand, a kind of aircraft 9 is also provided, including the engine system as described in any of the above, aircraft 9 further includes, machine body 91, air generator 1 is arranged at the machine body 91;Wing 92, connect with the machine body 91, turbofan engine 4 is arranged at the wing 92.

[0059] Specifically, the aircraft 9 can be but not limited to an airplane, and the machine body 91 is provided with the wing 92 on both sides respectively, and at least two turbofan engines 4 are arranged at the wing 92 on both sides of the machine body 91.

[0060] Obviously, the above embodiment is only an example for clearly illustrating, and is not limited to the implementation. Although the embodiments of the present application are described in conjunction with the drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present application, and such modifications and variations all fall within the scope defined by the present application.

Claims

1. An engine system characterized by, The utility model relates to a kind of turbofan engine, comprising: Air generator (1) is suitable for introducing external air and compressing; Air duct (2) is communicated with the air generator (1);The air duct (2) is suitable for extending inside the aircraft (9); Heat exchanger (3) is arranged with the part pipe section of the air duct (2), and it is suitable for cooling compressed air; Turbofan engine (4) is internally provided with gas collection chamber (42), and turbofan engine (4) further includes, Air inlet passage (61), one end is communicated with air duct (2), the other end is communicated with gas collection chamber (42), and it is suitable for introducing compressed air into turbofan engine (4); Compressor (43) is communicated with the gas collection chamber (42), and the compressor (43) is suitable for secondary compression to air; The turbofan engine (4) further includes, Baffle (41) is covered in the gas collection chamber (42), and the air inlet passage (61) is arranged through the baffle (41); Fan (5) is connected with first shaft (44), and the first shaft (44) is suitable for driving the fan (5) to rotate to introduce outer-duct airflow (7); Wherein, the air inlet passage (61) is suitable for introducing inner-duct airflow (8), and the inner-duct airflow (8) is independent of the outer-duct airflow (7); The air duct (2) is suitable for being arranged in the body (91) and wing (92) of the aircraft (9); The heat exchanger (3) is arranged in the wing (92) to cooperate with the pipe section of the air duct (2) in the wing (92).

2. The engine system of claim 1, wherein, Further comprising, hollow support plate (6) is internally provided with the air inlet passage (61);The hollow support plate (6) is arranged at the turbofan engine (4) and is arranged through the baffle (41); One end of the hollow support plate (6) is communicated with the air duct (2), and the other end is communicated with the gas collection chamber (42).

3. The engine system of claim 2, wherein, The gas collection chamber (42) is arranged around the axis of the first shaft (44).

4. The engine system of claim 1, wherein, Further comprising, combustion chamber (45) is communicated with the compressor (43), and the combustion chamber (45) is suitable for mixing and burning secondary pressurized air and fuel.

5. The engine system of claim 4, wherein, Further comprising, first turbine (46) is communicated with the combustion chamber (45); Second turbine (47) is located on the side, away from the combustion chamber (45), of the first turbine (46); Second shaft (48) is axially provided with a hole, and the second shaft (48) is sleeved on the peripheral portion of the first shaft (44) and is arranged in a spaced manner with the first shaft (44); Wherein, the first turbine (46) and the compressor (43) are connected with the second shaft (48) respectively; The second turbine (47) is connected with the first shaft (44), and the second turbine (47) is suitable for driving the first shaft (44) to rotate.

6. The engine system of claim 5, wherein, Further comprising, first rear support plate (51) is connected with the second shaft (48) by means of a rotary member, and is located beside the fan (5).

7. The engine system of claim 6, wherein, Further comprising, second rear support plate (49) is connected with the first shaft (44) by means of a rotary member, and is located on the side, away from the first turbine (46), of the second turbine (47).

8. An aircraft, characterized in that Further comprising, The engine system according to any one of claims 1 to 7. A fuselage (91) where the air generator (1) is provided; A wing (92) connected to the fuselage (91) where the turbofan engine (4) is provided.

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