Centrifugal compressor diffuser capable of exchanging heat

Abstract

The invention provides a centrifugal compressor diffuser capable of exchanging heat, and belongs to the technical field of diffusers, the centrifugal compressor diffuser comprises a diffuser shell, a heat exchange outer layer and a heat exchange inner layer which are sequentially arranged from outside to inside, a heat regenerator outer layer heat exchange cavity is formed between the diffuser shell and the heat exchange outer layer, and a heat regenerator inner layer heat exchange cavity is formed in the heat exchange inner layer; a heat exchange medium inlet and a heat exchange medium outlet are formed in the diffuser shell, a gas compressor radial diffuser blade and a gas compressor axial diffuser blade are arranged in an outer side annular cavity structure formed between the heat exchange inner layer and the heat exchange outer layer, and a radial supporting plate and an axial supporting plate are arranged in an inner side annular cavity structure. Axial diffuser heat exchange medium flow guide channels are arranged on the air compressor axial diffuser blades, axial supporting plate heat exchange medium flow guide channels and heat regenerator inner and outer layer heat exchange cavities are arranged on the axial supporting plates, the heat exchange medium flow guide channels are heat exchange medium flow paths, and the space between the heat exchange inner layer and the heat exchange outer layer is an air flow path. According to the scheme, the heat exchange efficiency is high, reliability is high, and compensation loss is small.

Description

Technical Field

[0001] The present application relates to the technical field of diffusers, and particularly to a centrifugal compressor diffuser capable of heat exchange. Background Art

[0002] The thermal management system of an aeroengine is responsible for designing the heat distribution among various components and systems of the engine, as well as between the aircraft and the engine, so as to achieve the purpose of improving energy utilization efficiency and realizing the optimal design of the system.

[0003] With the continuous improvement of the requirements for energy conservation, emission reduction, and environmental protection of engines in recent years, engine energy conservation and emission reduction technologies have become one of the most important directions for its technological development. Only about one-third of the energy released by engine fuel combustion is effectively utilized, and effectively recovering and utilizing the waste heat of gas turbine exhaust is the most effective way to promote and expand the development of gas turbines. For example, the SGT-300 gas turbine designed and manufactured by Siemens and Takuma is particularly suitable for combined heat and power generation. The high-temperature exhaust gas generated by the equipment is reused through a waste heat recovery device, so that the thermal efficiency reaches more than 95%. The generated steam or hot water can be used for industrial production and can also be combined with a steam turbine for a small combined cycle. With the development of the new generation of aeroengines towards wide airspace, wide speed range, longer flight time, multi-electrification, adaptive intelligence, etc., their energy consumption increases, but at the same time, a large amount of heat is dissipated or directly discharged into the atmosphere, resulting in great waste. However, introducing an intercooler and a regenerator into the traditional engine structure can effectively utilize the waste heat of the engine exhaust to improve its performance, but it will make the engine structure more complex, and at the same time, the manufacturing difficulty and research and development cost will increase significantly.

[0004] A heat exchanger with a conformal design to the compressor diffuser structure is a conformal structure that uses intermediate media such as water, therminol, or freon to transfer the heat of the gas turbine exhaust to the inlet end of the combustion chamber, reducing the weight cost on the basis of improving the thermal cycle efficiency of the gas turbine. With the intensification of the energy crisis and environmental pollution problems and the research and development of high-cost-effective thermoelectric materials, waste heat recovery technology has attracted much attention in the fields of automobiles, ships, industry, etc. Many developed countries are carrying out relevant research work. Japan even supports and develops waste heat recovery technology as an important energy and environmental strategic technology. However, the waste heat recovery technology based on loop heat pipes has not been applied and promoted in aeroengines.

[0005] Compared with simply introducing the intercooler and regenerator technologies, the heat exchange component with a conformal design to the compressor diffuser structure has the advantages of high heat exchange efficiency, high reliability, light weight, etc., and can be passed through. However, at present, in the field of aeroengines in China, there is a lack of relevant research and application of waste heat recovery technology suitable for aeroengines. Summary of the Invention

[0006] In view of this, the embodiments of the present application provide a heat-exchangeable centrifugal compressor diffuser to reduce the loss and waste of thermal energy in an aeroengine. Compared with the introduction of intercooler and recuperator technologies, the present application can recover and utilize the waste heat of the engine without affecting the overall layout of the core components of the aeroengine, improve the energy utilization efficiency, and achieve energy conservation and emission reduction.

[0007] The embodiments of the present application provide a heat-exchangeable centrifugal compressor diffuser, which includes a diffuser housing, a heat-exchange outer layer, and a heat-exchange inner layer arranged in sequence from outside to inside. The diffuser housing, the heat-exchange outer layer, and the heat-exchange inner layer are all arranged in an annular cavity structure. A recuperator outer-layer heat-exchange cavity is formed between the diffuser housing and the heat-exchange outer layer, and a recuperator inner-layer heat-exchange cavity is formed by the heat-exchange inner layer. A heat-exchange medium inlet and a heat-exchange medium outlet are provided on the outer peripheral wall of the diffuser housing, and the heat-exchange medium inlet and the heat-exchange medium outlet are arranged opposite to each other. A compressor radial diffuser vane and a compressor axial diffuser vane are arranged inside the outer annular cavity structure formed between the heat-exchange outer layer and the heat-exchange inner layer. A radial support plate and an axial support plate are arranged inside the inner annular cavity structure formed between the heat-exchange outer layer and the heat-exchange inner layer. An axial diffuser heat-exchange medium diversion channel is provided on the compressor axial diffuser vane, and an axial support plate heat-exchange medium diversion channel is provided on the axial support plate. The recuperator outer-layer heat-exchange cavity, the recuperator inner-layer heat-exchange cavity, the axial diffuser heat-exchange medium diversion channel, and the axial support plate heat-exchange medium diversion channel are all heat-exchange medium flow paths, and the space between the heat-exchange outer layer and the heat-exchange inner layer is an air flow path.

[0008] According to a specific implementation manner of the embodiments of the present application, a plurality of layers of first heat-exchange fins are arranged around the outer side of the radial support plate.

[0009] According to a specific implementation manner of the embodiments of the present application, a plurality of layers of second heat-exchange fins are arranged around the outer side of the axial support plate.

[0010] According to a specific implementation manner of the embodiments of the present application, the layer spacing of the second heat-exchange fins is set to 3-5 mm, and the thickness of the second heat-exchange fins is set to 0.5-1.5 mm.

[0011] According to a specific implementation manner of the embodiments of the present application, the second heat-exchange fins are arranged as annular heat-exchange fins.

[0012] According to a specific implementation manner of the embodiments of the present application, the thickness of the axial support plate is set to 3-4 mm.

[0013] According to a specific implementation manner of the embodiments of the present application, the maximum width of the axial diffuser heat-exchange medium diversion channel is set to 1-2 mm.

[0014] According to a specific implementation manner of the embodiments of the present application, the width of the axial support plate heat-exchange medium diversion channel is set to 1-2 mm.

[0015] According to a specific implementation of the embodiment of the present application, the structure of the axial diffuser heat exchange medium guide channel or the axial support plate heat exchange medium guide channel is set to a guide slot, a guide circular hole or a racetrack-type guide hole.

[0016] According to a specific implementation of the embodiment of the present application, the heat exchange medium flowing into the heat exchange medium inlet is set to thermal conductivity A.

[0017] Beneficial effects:

[0018] The heat-exchangeable centrifugal compressor diffuser in the embodiment of the present application is capable of recycling and utilizing the engine exhaust waste heat without affecting the structure of the core components of the aircraft engine. At the same time, the heat exchange structure that is conformally integrated with the centrifugal compressor diffuser structure has the advantages of high heat exchange efficiency, high reliability, and small compensation losses.

[0019] The high-temperature exhaust gas generated during the operation of the engine is used as a heat source, and the compressor outlet air is used as a cold source. The two are fully heat-exchanged through the intermediate medium to form a temperature difference, and the latent heat of vaporization of the intermediate medium is used to improve the heat transfer capacity. This application completes the design of a heat exchange structure that is conformally integrated with the centrifugal compressor diffuser structure, which can recover the waste heat of the gas turbine and transfer it to the inlet of the engine combustion chamber, effectively improving the thermal cycle efficiency of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 A structural diagram of a heat exchangeable centrifugal compressor diffuser according to an embodiment of the present invention;

[0022] Figure 2 A schematic diagram of a heat exchange medium inlet end of a heat exchangeable centrifugal compressor diffuser according to an embodiment of the present invention;

[0023] Figure 3 Schematic diagram of a heat exchange medium outflow end of a heat exchangeable centrifugal compressor diffuser according to an embodiment of the present invention;

[0024] Figure 4 A three-dimensional structural diagram of a heat exchangeable centrifugal compressor diffuser according to an embodiment of the present invention;

[0025] Figure 5 FIG. 4 is another three-dimensional structural diagram of a heat exchangeable centrifugal compressor diffuser according to an embodiment of the present invention.

[0026] In the figure: 1. Compressor radial diffuser vane; 2. Compressor axial diffuser vane; 3. Heat exchange medium inlet; 4. Axial support plate; 5. Radial support plate; 6. Outer heat exchange cavity of the regenerator; 7. Inner heat exchange cavity of the regenerator; 8. Axial diffuser heat exchange medium diversion channel; 9. Axial support plate heat exchange medium diversion channel; 10. Second heat exchange fin. Detailed implementation manners

[0027] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0028] The following uses specific specific examples to illustrate the implementation manners of the present application. 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 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. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present application.

[0029] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be obvious 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 the present 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 described herein can be used to implement the device and / or practice the method. In addition, this device and / or this method can be implemented using other structures and / or functions in addition to one or more of the aspects described herein.

[0030] It should also be noted that the drawings provided in the following embodiments only illustrate the basic concept of the present application in a schematic manner. The drawings only show the components related to the present application, rather than being drawn according to the number, shape and size of the components in actual implementation. The type, quantity and proportion of each component in its actual implementation can be an arbitrary change, and the component layout type may also be more complex.

[0031] 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 described aspects can be practiced without these specific details.

[0032] The present application embodiment provides a heat exchangeable centrifugal compressor diffuser, as shown below Figures 1 to 5 Describe in detail.

[0033] A heat exchangeable centrifugal compressor diffuser, referring to Figures 1 to 3 , including a diffuser shell, a heat exchange outer layer and a heat exchange inner layer arranged in sequence from outside to inside, the diffuser shell, the heat exchange outer layer and the heat exchange inner layer are all arranged as an annular cavity structure, a regenerator outer layer heat exchange cavity 6 is formed between the diffuser shell and the heat exchange outer layer, and a regenerator inner layer heat exchange cavity 7 is formed in the heat exchange inner layer. A heat exchange medium inlet 3 and a heat exchange medium outlet are arranged on the outer peripheral wall of the diffuser shell, and the heat exchange medium inlet 3 and the heat exchange medium outlet are arranged oppositely. The outer annular cavity structure formed between the heat exchange outer layer and the heat exchange inner layer is provided with a compressor radial diffuser blade 1 and a compressor radial diffuser blade 2. The turbine axial diffuser blade 2 has a radial support plate 5 and an axial support plate 4 inside the inner annular cavity structure formed between the heat exchange outer layer and the heat exchange inner layer. The compressor axial diffuser blade 2 is provided with an axial diffuser heat exchange medium guide channel 8, and the axial support plate 4 is provided with an axial support plate heat exchange medium guide channel 9. The regenerator outer layer heat exchange cavity 6, the regenerator inner layer heat exchange cavity 7, the axial diffuser heat exchange medium guide channel 8 and the axial support plate heat exchange medium guide channel 9 are all heat exchange medium flow paths, and the space between the heat exchange outer layer and the heat exchange inner layer is an air flow path.

[0034] The heat exchangeable centrifugal compressor diffuser in this embodiment adopts a conformal integrated design for the heat exchanger and the compressor diffuser. The heat exchange medium can be set to be a heat transfer medium A. The heat transfer medium A and other steam flow into the outlet side of the lower end through the outer heat exchange cavity 6 of the regenerator by gravity. The steam can also enter the outer heat exchange cavity 6 of the regenerator through the axial diffuser heat exchange medium guide channel 8 in the compressor axial diffuser blade 2 in the diffuser, and mix with the fluid in the outer heat exchange cavity 6 of the regenerator. The structure of the present application can recycle the waste heat of the engine exhaust without affecting the structure of the core components of the aircraft engine. At the same time, the heat exchange structure conformally integrated with the centrifugal compressor diffuser structure has the advantages of high heat exchange efficiency, high reliability, and small compensation loss. The high-temperature exhaust gas generated during the operation of the engine is used as a heat source, and the compressor outlet air is used as a cold source. The two fully exchange heat through the intermediate medium to form a temperature difference, and the latent heat of vaporization of the intermediate medium is used to improve the heat transfer capacity. This application completes the design of a heat exchange structure that is conformally integrated with the centrifugal compressor diffuser structure, which can recover the waste heat of the gas turbine and transfer it to the inlet of the engine combustion chamber, effectively improving the thermal cycle efficiency of the gas turbine.

[0035] In one embodiment, the outer side of the radial support plate 5 is surrounded by multiple layers of first heat exchange fins.

[0036] In one embodiment, the outer side of the axial support plate 4 is surrounded by multiple layers of second heat exchange fins 10 .

[0037] In specific implementation, by setting the first heat exchange fins or the second heat exchange fins 10, the heat exchange capacity of the heat exchanger can be further enhanced.

[0038] Furthermore, the layer spacing of the second heat exchange fins 10 is set to 3 - 5 mm, and the thickness of the second heat exchange fins 10 is set to 0.5 - 1.5 mm.

[0039] Furthermore, the second heat exchange fins 10 are set as annular heat exchange fins.

[0040] In one embodiment, the thickness of the axial support plate 4 is set to 3 - 4 mm.

[0041] In one embodiment, the maximum width of the axial diffuser heat exchange medium diversion channel 8 is set to 1 - 2 mm.

[0042] In one embodiment, the width of the axial support plate heat exchange medium diversion channel 9 is set to 1 - 2 mm. The axial support plate heat exchange medium diversion channel 9 in this embodiment is set as a leaf-shaped slit.

[0043] In one embodiment, the structure of the axial diffuser heat exchange medium diversion channel 8 or the axial support plate heat exchange medium diversion channel 9 is set as a diversion slit, a diversion round hole, or a runway-shaped diversion hole.

[0044] In one embodiment, the heat exchange medium flowing in from the heat exchange medium inlet 3 is set as Therminol A.

[0045] This application forms a heat exchanger that is conformal and integrated with a centrifugal compressor diffuser. The specific solution is as follows:

[0046] The heat exchange structure that is conformal and integrated with the centrifugal compressor diffuser structure is directly a thin-layer cavity structure attached to the compressor outlet air flow channel. The steam coming from the evaporator directly condenses on the channel wall surface, transfers the heat to the high-pressure flowing air on the other side of the wall surface, raises the air temperature, and the condensed liquid flows into the liquid collection port at the bottom by gravity or a circulation pump. The diffuser casing is designed as a sandwich casing, which serves as both the diffuser casing and forms the outer heat exchange cavity of the heat exchanger. The axial support plate 4 of the compressor diffuser and the heat exchange fins (the second heat exchange fins 10) of the heat exchanger are designed integrally. The axial support plate 4 of the compressor diffuser not only serves as the support plate of the compressor diffuser but also realizes the function of heat exchange between media such as Therminol A and the air in the compressor flow channel. The inflow direction of the heat exchange medium, the outflow direction of the heat exchange medium, the position of the annular air inlet, and the position of the annular air outlet are specifically referred to Figure 4 and Figure 5 .

[0047] Specifically, the outer heat exchange cavity of the heat exchanger and the outer casing of the compressor diffuser are designed with a conformal integrated structure. The outer casing of the diffuser casing is designed as a sandwich casing, which serves as the outer casing of the diffuser casing and also forms the outer heat exchange cavity 6 of the regenerator. Steam such as DOWTHERM A enters the outer heat exchange cavity 6 of the regenerator through the heat exchange medium inlet 3 on the outer casing of the compressor diffuser, flows into the outlet side at the lower end under the action of gravity, and then flows out through the heat exchange medium outlet.

[0048] Specifically, the axial compressor diffuser blades 2 and the heat exchange fins of the heat exchanger are integrally designed. On the basis of rectifying and diffusing the airflow at the compressor outlet, the axial compressor diffuser blades 2 also realize the heat exchange function between the airflow in the compressor flow path and DOWTHERM A. An axial diffuser heat exchange medium diversion channel 8 is opened in the blade, which can not only greatly improve the heat exchange effect of the axial compressor diffuser blades 2, but also enable the steam medium in the outer heat exchange cavity 6 of the regenerator to enter the inner heat exchange cavity 7 of the regenerator through the axial diffuser heat exchange medium diversion channel 8 at the inlet end under the action of pressure and gravity. The liquid medium in the inner heat exchange cavity 7 of the regenerator flows out to the outer heat exchange cavity 6 of the regenerator through the axial diffuser heat exchange medium diversion channel 8 at the outlet end.

[0049] Specifically, the inner heat exchange cavity 7 of the regenerator and the inner casing of the compressor diffuser are integrally designed. The inner casing of the compressor starts from the root of the radial compressor diffuser blade 1 and forms the inner heat exchange cavity 7 of the regenerator through the roots of the axial compressor diffuser blades 2, the axial support plates 4, and the radial support plates 5. When the heat exchange medium enters the inner heat exchange cavity 7 of the regenerator, it can fully exchange heat with the air in the main flow path of the compressor through the inner casing of the diffuser, increasing the heat exchange area and improving the heat exchange efficiency.

[0050] Specifically, the axial support plates 4 of the compressor diffuser and the heat exchange fins of the heat exchanger are integrally structured. The axial support plates 4 of the compressor diffuser not only serve as the support plates of the compressor diffuser but also realize the heat exchange between media such as DOWTHERM A and the air in the compressor flow path. An axial support plate heat exchange medium diversion channel 9 is opened in the axial support plate 4, enabling the media in the inner heat exchange cavity 7 and the outer heat exchange cavity 6 of the regenerator to flow fully with each other, increasing the heat exchange efficiency, and greatly improving the heat exchange effect of the axial support plate 4 as a heat exchange fin. At the same time, five layers of annular second heat exchange fins 10 are added to the axial support plates 4 of the compressor, which can greatly increase the heat exchange area and improve the heat exchange effect.

[0051] The embodiments provided by the present invention can recover and utilize the waste heat of the engine exhaust without affecting the structure of the core components of the aeroengine. At the same time, the heat exchange structure conformal integrated with the centrifugal compressor diffuser structure has the advantages of high heat exchange efficiency, high reliability, and small compensation loss.

[0052] The high-temperature exhaust gas generated during the operation of the engine is used as a heat source, and the compressor outlet air is used as a cold source. The two are fully heat-exchanged through the intermediate medium to form a temperature difference, and the latent heat of vaporization of the intermediate medium is used to improve the heat transfer capacity. This application completes the design of a heat exchange structure that is conformally integrated with the centrifugal compressor diffuser structure, which can recover the waste heat of the gas turbine and transfer it to the inlet of the engine combustion chamber, effectively improving the thermal cycle efficiency of the gas turbine.

[0053] The above is only a specific implementation 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 a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A heat-exchangeable centrifugal compressor diffuser, characterized in that, It includes a diffuser housing, an outer heat exchange layer, and an inner heat exchange layer arranged from outside to inside in sequence. The diffuser housing, the outer heat exchange layer, and the inner heat exchange layer are all arranged as annular cavity structures. A regenerator outer heat exchange cavity (6) is formed between the diffuser housing and the outer heat exchange layer, and the inner heat exchange layer forms a regenerator inner heat exchange cavity (7). A heat exchange medium inlet (3) and a heat exchange medium outlet are provided on the outer peripheral wall of the diffuser housing, and the heat exchange medium inlet (3) and the heat exchange medium outlet are arranged opposite to each other. Inside the outer annular cavity structure formed between the outer heat exchange layer and the inner heat exchange layer, there are compressor radial diffuser vanes (1) and compressor axial diffuser vanes (2). Inside the inner annular cavity structure formed between the outer heat exchange layer and the inner heat exchange layer, there are radial support plates (5) and axial support plates (4). An axial diffuser heat exchange medium diversion channel (8) is provided on the compressor axial diffuser vane (2), and an axial support plate heat exchange medium diversion channel (9) is provided on the axial support plate (4). The regenerator outer heat exchange cavity (6), the regenerator inner heat exchange cavity (7), the axial diffuser heat exchange medium diversion channel (8), and the axial support plate heat exchange medium diversion channel (9) are all heat exchange medium flow paths, and the space between the outer heat exchange layer and the inner heat exchange layer is an air flow path.

2. The heat-exchangeable centrifugal compressor diffuser according to claim 1, wherein Multiple layers of first heat exchange fins are arranged around the outside of the radial support plate (5).

3. The heat-exchangeable centrifugal compressor diffuser according to claim 1, wherein Multiple layers of second heat exchange fins (10) are arranged around the outside of the axial support plate (4).

4. The heat-exchangeable centrifugal compressor diffuser according to claim 3, characterized in that, The layer spacing of the second heat exchange fins (10) is set to 3 - 5 mm, and the thickness of the second heat exchange fins (10) is set to 0.5 - 1.5 mm.

5. The heat-exchangeable centrifugal compressor diffuser according to claim 3, characterized in that, The second heat exchange fins (10) are arranged as annular heat exchange fins.

6. The heat-exchangeable centrifugal compressor diffuser according to claim 1, characterized in that, The thickness of the axial support plate (4) is set to 3 - 4 mm.

7. The heat-exchangeable centrifugal compressor diffuser according to claim 1, wherein The maximum width of the axial diffuser heat exchange medium diversion channel (8) is set to 1 - 2 mm.

8. The heat-exchangeable centrifugal compressor diffuser according to claim 1, characterized in that, The width of the axial support plate heat exchange medium diversion channel (9) is set to 1 - 2 mm.

9. The heat-exchangeable centrifugal compressor diffuser according to claim 1, wherein, The structure of the axial diffuser heat exchange medium diversion channel (8) or the axial support plate heat exchange medium diversion channel (9) is set as a diversion slit, a diversion round hole, or a runway-shaped diversion hole.

10. The heat-exchangeable centrifugal compressor diffuser according to any one of claims 1-9, characterized in that, The heat exchange medium flowing in from the heat exchange medium inlet (3) is set as Therminol A.

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