Supercritical medium comprehensive heat management system of gas turbine engine

Abstract

The invention provides a gas turbine engine supercritical medium comprehensive heat management system, and belongs to the technical field of aero-engines, the gas turbine engine supercritical medium comprehensive heat management system comprises an anti-icing cap cover, an anti-icing support plate, a combustion chamber support plate, a tail cone, a compressor, a pressure regulating valve and a duct wall surface heat exchanger, the anti-icing cap cover, the anti-icing support plate, the combustion chamber support plate and the tail cone are arranged in sequence; an outlet of the compressor is connected with a first inlet of the combustion chamber supporting plate, a first outlet of the combustion chamber supporting plate is connected with an inlet of the pressure regulating valve, an outlet of the pressure regulating valve is connected with an inlet of the duct wall heat exchanger, an outlet of the duct wall heat exchanger is connected with a first inlet of the anti-icing supporting plate, and a second outlet of the anti-icing supporting plate is connected with an inlet of the anti-icing cap hood. The second inlet of the anti-icing supporting plate is connected with the outlet of the anti-icing cap cover, the second outlet of the combustion chamber supporting plate is connected with the tail cone inlet, and the outlet end of the tail cone is connected with the second inlet end of the combustion chamber supporting plate. The scheme of the invention has the characteristics of high integration, light weight and high cycle efficiency.

Description

Technical Field

[0001] This application relates to the technical field of aeroengines, and particularly to a comprehensive thermal management system for supercritical media of a gas turbine engine. Background Art

[0002] The infrared radiation signal of an aeroengine mainly comes from the visible wall surfaces of the nozzle (including the tail cone and combustion struts). The intensity of the radiation signal is related to the emissivity and temperature of the wall surface. Reducing the temperature of the visible wall surface is a common means of infrared radiation suppression. The main cold source for cooling the wall surface of the aeroengine tail nozzle is the bypass air or the air bled from the compressor rear. However, with the characteristics of high thrust-to-weight ratio and high cycle efficiency of aeroengines, the air bleed flow rate and the cooling quality of the bleed air are facing great constraints and challenges, which hinder the improvement of the engine's infrared suppression ability. On the other hand, during the actual operation of an aeroengine, the intake fairing struts and fairing caps are prone to icing problems. The common solution is to introduce high-temperature hot air from the compressor rear to the anti-icing system, and use the hot air to heat the fairing struts and fairing caps, thereby solving the icing problems faced during the engine operation. However, the high-temperature hot air used for anti-icing is directly discharged into the atmosphere after work, reducing the cycle performance of the engine. Summary of the Invention

[0003] In view of this, the embodiments of this application provide a comprehensive thermal management system for supercritical media of a gas turbine engine, which at least partially solves the problems of infrared suppression of the aeroengine nozzle and intake anti-icing existing in the prior art.

[0004] The embodiments of this application provide a comprehensive thermal management system for supercritical media of a gas turbine engine, including an anti-icing cap, an anti-icing strut, a combustion chamber strut, and a tail cone arranged in sequence, and further including a compressor, a pressure regulating valve, and a duct wall heat exchanger. The anti-icing cap, the anti-icing strut, the combustion chamber strut, the tail cone, and the duct wall heat exchanger are all arranged as conformal heat exchange structures through which supercritical media can flow;

[0005] The inlet end of the compressor is connected to the first outlet end of the anti-icing strut, the outlet end of the compressor is connected to the first inlet end of the combustion chamber strut, the first outlet end of the combustion chamber strut is connected to the inlet end of the pressure regulating valve, the outlet end of the pressure regulating valve is connected to the inlet end of the duct wall heat exchanger, the outlet end of the duct wall heat exchanger is connected to the first inlet end of the anti-icing strut, the second outlet end of the anti-icing strut is connected to the inlet end of the anti-icing cap, the second inlet end of the anti-icing strut is connected to the outlet end of the anti-icing cap, the second outlet end of the combustion chamber strut is connected to the inlet end of the tail cone, and the outlet end of the tail cone is connected to the second inlet end of the combustion chamber strut.

[0006] According to a specific implementation manner of an embodiment of the present application, the system further includes a medium storage tank, an emergency operation mode opening and closing valve, and an impact cooling nozzle that are connected in sequence. The impact cooling nozzle is arranged on the tail cone.

[0007] According to a specific implementation manner of an embodiment of the present application, the system further includes a two-way valve. The two-way valve is arranged between the inlet end of the compressor and the first outlet end of the anti-icing strut, and the two-way valve is also connected to the medium storage tank.

[0008] According to a specific implementation manner of an embodiment of the present application, the duct wall heat exchanger includes a first duct wall heat exchanger and a second duct wall heat exchanger arranged in parallel. The inlet ends of the first duct wall heat exchanger and the second duct wall heat exchanger are respectively connected to one end of a flow regulating valve, and the other end of the flow regulating valve is connected to the outlet end of a pressure regulating valve. The outlet ends of the first duct wall heat exchanger and the second duct wall heat exchanger are respectively connected to the first inlet end of the anti-icing strut.

[0009] According to a specific implementation manner of an embodiment of the present application, the conformal heat exchange structure is arranged as a sandwich structure, and a heat exchange channel for the flow of supercritical medium is provided inside the sandwich structure.

[0010] According to a specific implementation manner of an embodiment of the present application, the structure of the heat exchange channel is arranged as a circular channel, a square channel, or a square-twisted channel, and the square-twisted channel is obtained by rotating the square channel circumferentially.

[0011] According to a specific implementation manner of an embodiment of the present application, a plurality of combustion chamber struts are circumferentially distributed. The plurality of combustion chamber struts are divided into two groups, namely a first group of combustion chamber struts and a second group of combustion chamber struts. The inlet end of the first group of combustion chamber struts is used as the first inlet end of the combustion chamber strut, the outlet end of the second group of combustion chamber struts is used as the first outlet end of the combustion chamber strut, the inlet end of the second group of combustion chamber struts is used as the second inlet end of the combustion chamber strut, the outlet end of the first group of combustion chamber struts is used as the second outlet end of the combustion chamber strut, and a bypass valve is provided between the outlet end of the first group of combustion chamber struts and the inlet end of the second group of combustion chamber struts.

[0012] According to a specific implementation manner of an embodiment of the present application, a plurality of anti-icing struts are circumferentially distributed. The plurality of anti-icing struts are divided into two groups, namely a first group of anti-icing struts and a second group of anti-icing struts. The inlet end of the first group of anti-icing struts is used as the first inlet end of the anti-icing strut, the outlet end of the second group of anti-icing struts is used as the first outlet end of the anti-icing strut, the inlet end of the second group of anti-icing struts is used as the second inlet end of the anti-icing strut, the outlet end of the first group of anti-icing struts is used as the second outlet end of the anti-icing strut, and a bypass valve is provided between the outlet end of the first group of anti-icing struts and the inlet end of the second group of anti-icing struts.

[0013] According to a specific implementation manner of an embodiment of the present application, the inlet end of the anti-icing hood or the inlet end of the tail cone is disposed at the inner conical tip, and the heat exchange channel of the anti-icing hood or the heat exchange channel of the tail cone is set as a straight channel or a spiral curved channel. The straight channel is laid in an umbrella shape from the inlet end to the side wall surface, and the spiral curved channel is laid in a spiral winding manner from the inlet end to the side wall surface.

[0014] According to a specific implementation manner of an embodiment of the present application, a flow distribution ring is provided at the inlet end of the duct wall heat exchanger, and a flow convergence ring is provided at the outlet end of the duct wall heat exchanger.

[0015] Beneficial effects:

[0016] Traditional backward infrared signal suppression uses shielding and cooling as means, but the cooling is restricted by the temperature of the bleed air, and the infrared characteristics cannot disappear in an emergency. On the other hand, traditional anti-icing systems use bleed air after the compressor, and after being heated, the hood and the anti-icing strut are directly discharged into the atmosphere, wasting some energy. However, the infrared suppression and anti-icing integrated control system solution based on supercritical media proposed by the present invention uses supercritical media refrigerant to transfer heat, thereby reducing the hot air bleed of the anti-icing strut and the anti-icing hood and the cold air bleed of the combustion strut and the tail cone, which can further improve the engine cycle efficiency. Since the heat exchanger is integrated on the engine components in this system without adding an additional heat exchanger, it has the advantages of easy implementation and lightweight.

[0017] The present invention integrates the infrared signal suppression and the anti-icing system, which not only solves the problem of backward infrared signal suppression, but also solves the problem of icing at the engine inlet. Since this system does not add an additional heat exchanger, reduces the anti-icing air pipe, the anti-icing system no longer draws hot air after the compressor, and the combustion strut and the tail cone do not need to draw cold air, having the advantages of high integration, lightweight, and high cycle efficiency. Brief description of the drawings

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0019] Figure 1 It is a schematic diagram of Embodiment 1 of a supercritical medium integrated thermal management system for a gas turbine engine according to the present invention;

[0020] Figure 2 It is a schematic diagram of Embodiment 2 of a supercritical medium integrated thermal management system for a gas turbine engine according to the present invention;

[0021] Figure 3Schematic diagram of the third embodiment of the supercritical medium integrated thermal management system for a gas turbine engine according to the present invention;

[0022] Figure 4 Schematic diagram of the fourth embodiment of the supercritical medium integrated thermal management system for a gas turbine engine according to the present invention;

[0023] Figure 5 Schematic structural diagram of the channel of the conformal heat exchange structure according to an embodiment of the present invention;

[0024] Figure 6 Supercritical medium flow pattern in the strut according to an embodiment of the present invention;

[0025] Figure 7 Two supercritical medium flow patterns in the anti-icing cowl and tail cone according to an embodiment of the present invention;

[0026] Figure 8 Two supercritical fluid flow patterns in the duct wall heat exchanger according to an embodiment of the present invention;

[0027] In the figure: 1. Compressor, 2. Combustion chamber strut, 3. Tail cone, 4. Pressure regulating valve, 5. Duct wall heat exchanger, 6. Anti-icing strut, 7. Anti-icing cowl, 8. Storage tank, 9. Emergency operation mode opening and closing valve, 10. Impingement cooling nozzle, 11. Compressor, 12. Combustion chamber, 13. Turbine, 14. Two-way valve, 15. Flow regulating valve. Specific implementation manners

[0028] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0029] The following illustrates the implementation manners of the present application through specific specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without making creative efforts belong to the scope of protection of the present application.

[0030] Note that the following description details various aspects of embodiments within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on this application, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement a device and / or practice a method. Additionally, this device can be implemented and this method can be practiced using other structures and / or functionality in addition to one or more of the aspects set forth herein.

[0031] It should also be noted that the diagrams provided in the following embodiments only schematically illustrate the basic concept of this application. The diagrams only show the components related to this application and are not drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0032] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the aspects can be practiced without these specific details.

[0033] An embodiment of this application provides a comprehensive thermal management system for a supercritical medium of a gas turbine engine, which will be described in detail below with reference to the drawings.

[0034] A comprehensive thermal management system for a supercritical medium of a gas turbine engine includes an anti-icing cowl 7, an anti-icing strut 6, a compressor 11, a combustion chamber 12, a turbine 13, a combustion chamber strut 2, and a tail cone 3 arranged in sequence. It also includes a compressor 1, a pressure regulating valve 4, and a duct wall heat exchanger 5. The anti-icing cowl 7, the anti-icing strut 6, the combustion chamber strut 2, the tail cone 3, and the duct wall heat exchanger 5 are all configured as conformal heat exchange structures through which the supercritical medium can flow;

[0035] The inlet end of the compressor 1 is connected to the first outlet end of the anti-icing strut 6, the outlet end of the compressor 1 is connected to the first inlet end of the combustion chamber strut 2, the first outlet end of the combustion chamber strut 2 is connected to the inlet end of the pressure regulating valve 4, the outlet end of the pressure regulating valve 4 is connected to the inlet end of the duct wall heat exchanger 5, the outlet end of the duct wall heat exchanger 5 is connected to the first inlet end of the anti-icing strut 6, the second outlet end of the anti-icing strut 6 is connected to the inlet end of the anti-icing cowl 7, the second inlet end of the anti-icing strut 6 is connected to the outlet end of the anti-icing cowl 7, the second outlet end of the combustion chamber strut 2 is connected to the inlet end of the tail cone 3, and the outlet end of the tail cone 3 is connected to the second inlet end of the combustion chamber strut 2.

[0036] In this embodiment, a supercritical medium is used as the refrigerant, and the anti-icing system, strut, and infrared suppression of the aft fuselage are combined to solve the problems of anti-icing of the front-end components and infrared suppression of the hot-end components at the tail end. Specifically, in the normal operating mode, in this embodiment, the anti-icing cowl 7, anti-icing strut 6, duct heat exchange wall 5, combustion strut 2, and aft fuselage 3 are made into a sandwich structure, and then the compressor 1, pressure regulating valve 4 and the above components are connected in series through pipelines, using the supercritical medium as the refrigerant to form a Brayton closed-cycle system. The compressor 1 drives the refrigerant to circulate. The low-temperature refrigerant in the cycle cools the combustion chamber strut 2 and the aft fuselage 3, playing a role in infrared suppression. The high-temperature refrigerant after absorbing heat heats the anti-icing strut 6 and the anti-icing cowl 7, playing a role in anti-icing.

[0037] Further, to cope with the emergency operating mode, the system further includes a medium storage tank 8, an emergency operating mode on-off valve 9, and an impingement cooling nozzle 10 connected in sequence. The impingement cooling nozzle 10 is arranged on the aft fuselage 3.

[0038] In the emergency operating mode, the supercritical medium refrigerant in the storage tank 8 is directly sprayed onto the wall of the aft fuselage 3 through pipelines and valves for rapid cooling, thereby suppressing the infrared signal.

[0039] Further, the system further includes a two-way valve 14. The two-way valve 14 is arranged between the inlet end of the compressor 1 and the first outlet end of the anti-icing strut 6, and the two-way valve 14 is also connected to the medium storage tank 8.

[0040] In this embodiment, the other side of the storage tank 8 is connected to the closed cycle through the two-way valve 14. The flow rate of the supercritical medium in the closed cycle can be adjusted through the storage tank 8 and the rotational speed of the compressor 1 to match different operating states.

[0041] Further, the duct wall heat exchanger 5 includes a first duct wall heat exchanger 5 and a second duct wall heat exchanger 5 arranged in parallel. The inlet ends of the first duct wall heat exchanger 5 and the second duct wall heat exchanger 5 are respectively connected to one end of a flow regulating valve 15. The other end of the flow regulating valve 15 is connected to the outlet end of the pressure regulating valve 4. The outlet ends of the first duct wall heat exchanger 5 and the second duct wall heat exchanger 5 are respectively connected to the first inlet end of the anti-icing strut 6.

[0042] In this embodiment, by arranging the duct wall heat exchanger 5 in a parallel form, according to the system requirements, different flow rates can be allocated to the parallel-mode heat exchangers through the supercritical medium flow regulating valve 15, thereby improving the cycle efficiency of the closed-cycle system and reducing energy loss.

[0043] Next, the structural form of the above system will be described in detail with specific embodiments.

[0044] Embodiment 1

[0045] AsFigure 1 As shown in the figure, in the normal working mode, the low-temperature supercritical medium is compressed and pressurized by the compressor 1. The high-pressure and low-temperature supercritical medium flows into the combustion chamber strut 2 and the tail cone 3 to cool them, thereby suppressing the infrared signals of the combustion chamber strut 2 and the tail cone 3. Then, the high-temperature and high-pressure supercritical medium flows through the pressure regulating valve 4 to reduce the pressure. Subsequently, the supercritical medium flows through the duct wall heat exchanger 5, the anti-icing strut 6, and the anti-icing cowl 7 in sequence and is cooled by the air. At the same time, the anti-icing strut 6 and the anti-icing cowl 7 are heated, thereby achieving the purpose of anti-icing. Finally, the cooled supercritical medium enters the compressor 1 again to be compressed, thereby forming a closed cycle. During the working process, by adjusting the rotation speed of the compressor 1, it can adapt to different working conditions. In the emergency working mode, the emergency working mode opening and closing valve 9 is opened, and the supercritical medium in the storage tank 8 is sprayed onto the inner wall surface of the tail cone 3 and the inner wall surface of the strut through the supercritical medium impact cooling nozzle 10, thereby quickly reducing the wall temperature and achieving the purpose of quickly eliminating the infrared signal.

[0046] Embodiment 2

[0047] As Figure 2 shown, on the basis of Embodiment 1, a supercritical medium two-way valve 14 is added between the front of the compressor 1 and the gas storage tank. According to the system requirements, this valve fills or stores the supercritical medium in the closed-cycle flow path to adjust the circulation flow rate, so that the system can adapt to a wider range of working conditions.

[0048] Embodiment 3

[0049] As Figure 3 shown, on the basis of Embodiment 2, the duct wall heat exchanger 5 is changed from a series mode to a distributed parallel mode, and according to the system requirements, different flow rates are allocated to the parallel-mode heat exchanger through the supercritical medium flow regulating valve 15, thereby improving the circulation efficiency of the closed-cycle system and reducing the energy loss.

[0050] Embodiment 4

[0051] As Figure 4 shown, on the basis of Embodiment 3, the supercritical medium two-way valve 14 is removed, partially sacrificing the flow rate regulation ability of the closed-cycle system, but decoupling the open type and the closed type, which will reduce the control difficulty of the system and enhance the system robustness.

[0052] In one embodiment, the conformal heat exchange structure is set as a sandwich structure, and a heat exchange channel for the flow of the supercritical medium is provided inside the sandwich structure.

[0053] Furthermore, the structure of the heat exchange channel is set as a circular channel, a square channel, or a square twist channel, and the square twist channel is obtained by rotating the square channel circumferentially.

[0054] In specific implementation, in the system of the present application, the combustor strut 2, the tail cone 3, the duct wall heat exchanger 5, the anti-icing strut 6, and the anti-icing cowl 7 are all conformal heat exchange structures. Among them, the supercritical medium in the combustor strut 2 and the tail cone 3 is heated by the combustion gas; the supercritical medium in the duct wall heat exchanger 5, the anti-icing strut 6, and the anti-icing cowl 7 is cooled by the air. The conformal heat exchange structure is formed by arranging multiple channels inside the original engine-related components, and the structure form of a single channel is as shown in Figure 5 shown, mainly divided into the circular channel in Figure a), the square channel in Figure b), and the square-twisted channel in Figure c). The square-twisted channel in Figure c) is formed by rotating the square channel in Figure b) along the circumferential direction, which can further improve the heat exchange efficiency.

[0055] In one embodiment, the flow form of the supercritical medium in the combustor strut 2 is set. A plurality of combustor struts 2 are circumferentially distributed. The plurality of combustor struts 2 are divided into two groups, namely the first group of combustor struts 2 and the second group of combustor struts 2. The inlet end of the first group of combustor struts 2 is used as the first inlet end of the combustor strut 2, the outlet end of the second group of combustor struts 2 is used as the first outlet end of the combustor strut 2, the inlet end of the second group of combustor struts 2 is used as the second inlet end of the combustor strut 2, the outlet end of the first group of combustor struts 2 is used as the second outlet end of the combustor strut 2, and a bypass valve is provided between the outlet end of the first group of combustor struts 2 and the inlet end of the second group of combustor struts 2.

[0056] Specifically, referring to Figure 6 , since the combustor strut 2 is located in the annular channel formed by the engine casing and the central bearing cavity and is evenly arranged along the circumferential direction. Figure 6 shows two flow forms of the supercritical medium in the struts. Taking the combustor strut 2 in this embodiment as an example, a plurality of combustor struts 2 are circumferentially distributed. The supercritical medium from the compressor 1 is divided into multiple paths at the inlet. The inlet end of the first group of combustor struts 2 is connected to the outlet end of the compressor 1, the outlet end of the first group of combustor struts 2 is connected to the inlet end of the tail cone 3, the outlet end of the tail cone 3 is connected to the inlet end of the second group of combustor struts 2, and the outlet end of the second group of combustor struts 2 is connected to the inlet end of the pressure regulating valve 4. Therefore, the flow direction of the supercritical medium is as follows: in half of the combustor struts 2 (the first group of combustor struts 2), it flows radially towards the center, and then converges into one path. Subsequently, part of the supercritical medium flows into the tail cone 3, and the rest of the supercritical medium flows away through the bypass valve, and then the two paths converge into one path. Then, the supercritical medium is divided into multiple paths again, and flows radially centrifugally in the other half of the combustor struts 2 (the second group of combustor struts 2), and finally converges into one path and flows towards the pressure regulating valve 4.

[0057] In one embodiment, the flow pattern of the supercritical medium in the anti-icing strut 6 is set. A plurality of anti-icing struts 6 are circumferentially distributed. The plurality of anti-icing struts 6 are divided into two groups, namely the first group of anti-icing struts 6 and the second group of anti-icing struts 6. The inlet end of the first group of anti-icing struts 6 is used as the first inlet end of the anti-icing strut 6, the outlet end of the second group of anti-icing struts 6 is used as the first outlet end of the anti-icing strut 6, the inlet end of the second group of anti-icing struts 6 is used as the second inlet end of the anti-icing strut 6, the outlet end of the first group of anti-icing struts 6 is used as the second outlet end of the anti-icing strut 6, and a bypass valve is provided between the outlet end of the first group of anti-icing struts 6 and the inlet end of the second group of anti-icing struts 6.

[0058] Specifically, referring to Figure 6 , since the anti-icing strut 6 is located in the annular channel formed by the engine casing and the central bearing cavity and is evenly arranged circumferentially. Figure 6 Two flow patterns of the supercritical medium in the struts are shown. Taking the anti-icing strut 6 in this embodiment as an example, several anti-icing struts 6 are circumferentially distributed. The supercritical medium from the duct wall heat exchanger 5 is divided into multiple paths at the inlet. The inlet end of the first group of anti-icing struts 6 is connected to the outlet end of the duct wall heat exchanger 5, the outlet end of the first group of anti-icing struts 6 is connected to the inlet end of the anti-icing cap 7, the outlet end of the anti-icing cap 7 is connected to the inlet end of the second group of anti-icing struts 6, and the outlet end of the second group of anti-icing struts 6 is connected to the inlet end of the compressor 1. Therefore, the flow direction of the supercritical medium is as follows: it flows radially centripetally in half of the anti-icing struts 6 (the first group of anti-icing struts 6) and then converges into one path. Subsequently, part of the supercritical medium flows into the anti-icing cap 7, and the rest of the supercritical medium flows away through the bypass valve, and then the two paths converge into one path. Then, the supercritical medium is divided into multiple paths again and flows radially centrifugally in the other half of the anti-icing struts 6 (the second group of anti-icing struts 6) and finally converges into one path and flows to the compressor 1.

[0059] Furthermore, the flow pattern of the supercritical medium in the anti-icing cap 7 and the tail cone 3 is set. The inlet end of the anti-icing cap 7 or the inlet end of the tail cone 3 is arranged at the inner tip, and the heat exchange channel of the anti-icing cap 7 or the heat exchange channel of the tail cone 3 is set as a straight channel or a spiral curved channel. The straight channel is laid in an umbrella shape from the inlet end to the side wall surface, and the spiral curved channel is laid in a spiral winding manner from the inlet end to the side wall surface.

[0060] Specifically, in the engine, both the anti-icing cap 7 and the tail cone 3 are conical thin-walled components, and their structural forms are highly similar. Figure 7Shows two flow forms of the supercritical medium in the anti-icing cap 7 and the caudal vertebra 3: a) In the figure, the supercritical medium flows in from the inner tip of the cap or the caudal vertebra 3, and then flows out in an umbrella shape to the surroundings. The internal heat exchange channel is a straight channel; b) In the figure, the supercritical medium flows in from the inner tip of the cap or the caudal vertebra 3, and then flows circumferentially and spirally towards the bottom of the cone. The internal heat exchange channel is a spiral curved channel.

[0061] Furthermore, the flow form of the supercritical medium in the duct wall heat exchanger 5 is set. A flow distribution ring is provided at the inlet end of the duct wall heat exchanger 5, and a flow convergence ring is provided at the outlet end of the duct wall heat exchanger 5.

[0062] During specific implementation, the engine duct wall is in the form of an annular cylinder structure. By arranging the supercritical fluid channel in the duct wall structure, the duct wall heat exchanger 5 is formed. Figure 8 Shows two flow forms of the supercritical fluid in the duct wall heat exchanger 5: Figure 8 Figure a) in it shows that in the duct wall where the cooling channels are evenly distributed circumferentially, the supercritical fluid from the expansion valve (pressure regulating valve 4) first flows into the flow distribution ring, then flows axially through the cooling channels, and finally the fluid is collected by the flow convergence ring and then flows out; Figure 8 Figure b) in it is different from figure a). The duct wall heat exchanger 5 with a longer flow path is axially divided into two duct wall heat exchangers 5 with shorter flow paths. After the supercritical fluid flows in, the flow rate of the two heat exchangers is first distributed by the flow regulating valve 15. The two paths of fluid flow through the flow distribution ring, cooling channels, and flow convergence ring respectively through their own duct wall heat exchangers 5, and finally converge into one path and flow out. Through the distributed arrangement of this heat exchanger, the total heat exchange amount of the supercritical fluid can be effectively adjusted, thereby improving the robustness and working range of the system.

[0063] In the embodiment provided by the present invention, the infrared signal suppression is combined with the requirements of the anti-icing system. Using the supercritical fluid as the medium for heat transfer, the heat of the combustion chamber strut 2 and the caudal vertebra 3 is transported to the anti-icing strut 6 and the anti-icing cap 7, thereby achieving the effects of cooling the combustion chamber strut 2 and the caudal vertebra 3 and heating the anti-icing strut 6 and the anti-icing cap 7, and finally achieving the purpose of infrared signal suppression and preventing icing at the engine intake section.

[0064] The whole system is divided into a normal working mode (long-term) and an emergency working mode (short-term). In the normal working mode, while suppressing the infrared radiation signal on the wall surface of the tail nozzle, the problem of anti-icing of aero-engines is solved simultaneously through the collection, transmission and release of heat. Different from the conventional thermal management system, in this solution, the cold-end and hot-end heat exchangers are integrated on the engine combustion chamber struts 2, the tail cone 3, the anti-icing struts 6 and the anti-icing cowl 7, which is beneficial to the lightweight of the system and further improves the comprehensive energy utilization efficiency of the engine; in the emergency working mode, the supercritical medium refrigerant is directly sprayed onto the inner surface of the tail cone 3 and the struts, quickly reducing the temperature of the combustion struts and the tail cone 3 and quickly reducing the infrared signal to achieve the effect of emergency avoidance.

[0065] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A comprehensive thermal management system for supercritical media in a gas turbine engine, characterized in that, It includes an anti-icing cowling (7), an anti-icing strut (6), a combustion chamber strut (2) and a tail cone (3) arranged in sequence, and also includes a compressor (1), a pressure regulating valve (4) and a duct wall heat exchanger (5). The anti-icing cowling (7), the anti-icing strut (6), the combustion chamber strut (2), the tail cone (3) and the duct wall heat exchanger (5) are all arranged as conformal heat exchange structures through which supercritical media can flow; The inlet end of the compressor (1) is connected to the first outlet end of the anti-icing strut (6), the outlet end of the compressor (1) is connected to the first inlet end of the combustion chamber strut (2), the first outlet end of the combustion chamber strut (2) is connected to the inlet end of the pressure regulating valve (4), the outlet end of the pressure regulating valve (4) is connected to the inlet end of the duct wall heat exchanger (5), the outlet end of the duct wall heat exchanger (5) is connected to the first inlet end of the anti-icing strut (6), the second outlet end of the anti-icing strut (6) is connected to the inlet end of the anti-icing cowling (7), the second inlet end of the anti-icing strut (6) is connected to the outlet end of the anti-icing cowling (7), the second outlet end of the combustion chamber strut (2) is connected to the inlet end of the tail cone (3), and the outlet end of the tail cone (3) is connected to the second inlet end of the combustion chamber strut (2).

2. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 1, characterized in that The system also includes a medium storage tank (8), an emergency operation mode on-off valve (9) and an impingement cooling nozzle (10) connected in sequence, and the impingement cooling nozzle (10) is arranged on the tail cone (3).

3. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 2, wherein The system also includes a two-way valve (14), and the two-way valve (14) is arranged between the inlet end of the compressor (1) and the first outlet end of the anti-icing strut (6), and the two-way valve (14) is also connected to the medium storage tank (8).

4. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 1, characterized in that, The duct wall heat exchanger (5) includes a first duct wall heat exchanger (5) and a second duct wall heat exchanger (5) arranged in parallel. The inlet ends of the first duct wall heat exchanger (5) and the second duct wall heat exchanger (5) are respectively connected to one end of a flow regulating valve (15), the other end of the flow regulating valve (15) is connected to the outlet end of the pressure regulating valve (4), and the outlet ends of the first duct wall heat exchanger (5) and the second duct wall heat exchanger (5) are respectively connected to the first inlet end of the anti-icing strut (6).

5. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 1, characterized in that, The conformal heat exchange structure is arranged as a sandwich structure, and a heat exchange channel through which supercritical media flow is arranged inside the sandwich structure.

6. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 5, wherein The structure of the heat exchange channel is arranged as a circular channel, a square channel or a square twist channel, and the square twist channel is obtained by rotating the square channel along the circumferential direction.

7. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 1, characterized in that A plurality of the combustion chamber struts (2) are circumferentially distributed. The plurality of combustion chamber struts (2) are divided into two groups, namely the first group of combustion chamber struts (2) and the second group of combustion chamber struts (2). The inlet end of the first group of combustion chamber struts (2) serves as the first inlet end of the combustion chamber struts (2), the outlet end of the second group of combustion chamber struts (2) serves as the first outlet end of the combustion chamber struts (2), the inlet end of the second group of combustion chamber struts (2) serves as the second inlet end of the combustion chamber struts (2), the outlet end of the first group of combustion chamber struts (2) serves as the second outlet end of the combustion chamber struts (2), and a bypass valve is provided between the outlet end of the first group of combustion chamber struts (2) and the inlet end of the second group of combustion chamber struts (2).

8. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 1, characterized in that, A plurality of the anti-icing struts (6) are circumferentially distributed. The plurality of anti-icing struts (6) are divided into two groups, namely the first group of anti-icing struts (6) and the second group of anti-icing struts (6). The inlet end of the first group of anti-icing struts (6) serves as the first inlet end of the anti-icing struts (6), the outlet end of the second group of anti-icing struts (6) serves as the first outlet end of the anti-icing struts (6), the inlet end of the second group of anti-icing struts (6) serves as the second inlet end of the anti-icing struts (6), the outlet end of the first group of anti-icing struts (6) serves as the second outlet end of the anti-icing struts (6), and a bypass valve is provided between the outlet end of the first group of anti-icing struts (6) and the inlet end of the second group of anti-icing struts (6).

9. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 5, wherein, The inlet end of the anti-icing cowl (7) or the inlet end of the tail cone (3) is arranged at the inner conical tip. The heat exchange channel of the anti-icing cowl (7) or the heat exchange channel of the tail cone (3) is arranged as a straight channel or a spiral curved channel. The straight channel is laid in an umbrella shape from the inlet end to the side wall surface, and the spiral curved channel is laid in a spiral winding manner from the inlet end to the side wall surface.

10. The supercritical medium integrated thermal management system for a gas turbine engine according to claim 1, wherein A flow distribution ring is provided at the inlet end of the duct wall heat exchanger (5), and a flow convergence ring is provided at the outlet end of the duct wall heat exchanger (5).

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