Turbine rear support plate in oil-gas matching form and aero-engine

Abstract

The present application relates to the technical field of engine, and provides a turbine rear support plate in oil-gas matching form and an aero-engine.The turbine rear support plate in oil-gas matching form comprises a support plate body, the support plate body has a cavity, part of the support plate body is recessed into the cavity, a backflow area is formed in the recessed position, and the cavity is used for spraying cooling gas and fuel to the backflow area.The turbine rear support plate in oil-gas matching form can improve the ignition speed and combustion stability of the backflow area of the support plate body by introducing high-oxygen-content cooling gas after the core fan, and the oil-gas matching form meets the requirement of low-oxygen-content inflow combustion of a new generation of aero-engine wide-range afterburner.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and more particularly to a turbine rear support plate of an oil-gas matching type and an aero engine. Background Technology

[0002] The core requirement of the new generation of advanced aero engines is to balance the economy of low-speed subcruise (0.8 Ma), the economy and acceleration of medium-speed supersonic flight (1.3 to 2.5 Ma), and the continuous high thrust requirements of high-speed flight (2.5 to 5.0 Ma) within the airspace of 0-30km and the speed range of 0-5 Ma. Therefore, its design embodies the design concept of large flow rate, high throttle ratio, synchronous combined regulation of bypass ratio and pressure ratio, and high turbine inlet temperature across the entire speed range.

[0003] Due to the high efficiency of the main combustion chamber of the new generation of advanced aero engines, the oxygen content at the inlet of its afterburner is much lower than that of the traditional afterburner. Furthermore, due to the overall requirements of the aero engines mentioned above, the afterburner needs to organize combustion directly in the internal airflow. This means that the current fuel-air matching method cannot be directly used in the afterburner of the new generation of aero engines. Summary of the Invention

[0004] This invention provides a turbine rear support plate and an aero engine with an oil-gas matching configuration, in order to solve the defects of existing oil-gas matching configurations in the prior art that cannot meet the requirements of the next generation of aero engines.

[0005] The present invention provides a turbine rear support plate of oil-gas matching type, including a support plate body, the support plate body having a cavity, a portion of the support plate body being recessed into the cavity to form a recirculation zone, the cavity being used to inject cooling gas and fuel into the recirculation zone.

[0006] According to the present invention, a turbine rear support plate of oil-gas matching type includes a first plate and a second plate. The first plate and the second plate are arranged perpendicularly to form the recirculation zone. The first plate is provided with a first through hole, and the second plate is provided with a second through hole. Both the first through hole and the second through hole are in communication with the cavity. The first through hole is used to inject fuel into the recirculation zone, and the second through hole is used to inject cooling gas into the recirculation zone.

[0007] According to the present invention, in a turbine rear support plate of the form of oil-gas matching, at least one of the first through hole and the second through hole is inclined toward the other.

[0008] According to the present invention, a turbine rear support plate of the form of oil-gas matching is provided, wherein the first plate body and the second plate body are configured to form a bending portion, and the support plate body includes a pair of the bending portions, the pair of bending portions being symmetrically arranged about the axis of the support plate body, so that the support plate body forms two recirculation zones.

[0009] According to the present invention, a turbine rear support plate of the form of oil-gas matching is provided, the support plate body further includes a first bending plate and a second bending plate, the first bending plate is connected to a pair of first plate bodies, the second bending plate is connected to a pair of second plate bodies, and the space between the first bending plate, the pair of bending portions and the second bending plate forms the cavity.

[0010] According to the present invention, a turbine rear support plate of oil-gas matching type includes a cavity comprising a first cavity, a second cavity, and a third cavity, wherein the first cavity, the second cavity, and the third cavity are sequentially connected; the fuel is injected from the first cavity, and the cooling gas is injected from the second cavity.

[0011] According to the present invention, a turbine rear support plate of the oil-gas matching type further includes a pair of fuel lines, the pair of fuel lines being disposed in the first cavity, each of the fuel lines being used to inject fuel through a first through hole on the first plate; each of the fuel lines includes: a main fuel line and a plurality of fuel branch lines, the main fuel line being disposed in the first cavity, and each of the fuel branch lines having its two ends respectively connected to the main fuel line and a first through hole.

[0012] According to the present invention, in a turbine rear support plate of oil-gas matching type, the bend of the first bent plate is a pointed tip, and the first bent plate is streamlined.

[0013] According to the present invention, in a turbine rear support plate of the form of oil-gas matching, the distance between the opposite sides of the second bent plate gradually increases along the extension direction of the cavity.

[0014] The present invention also provides an aero engine, including a main combustion chamber, a turbine, a cooler, and an afterburner; the main combustion chamber is used to generate high-temperature and high-pressure gas, the gas drives the turbine to rotate, the turbine has a turbine rear support plate of the oil-gas matching form as described above, the cooler is connected to the cavity of the turbine rear support plate, and the afterburner is located downstream of the turbine rear support plate.

[0015] The turbine rear support plate with oil-gas matching provided in this embodiment of the invention can significantly improve the ignition speed and combustion stability of the recirculation zone of the support plate body by introducing high oxygen content cooling gas after the core fan. The oil-gas matching form meets the requirements of the wide-range afterburner of the new generation of aero engines for low oxygen content incoming flow combustion. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of the turbine rear support plate with oil-gas matching provided by the present invention.

[0018] Figure label:

[0019] 1. Support plate body; 11. First plate; 12. Second plate; 13. First bending plate; 14. Second bending plate; 15. First cavity; 16. Second cavity; 17. Third cavity; 18. Fuel main pipeline; 20. Return zone; 111. First through hole; 112. Second through hole. Detailed Implementation

[0020] The embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and should not be construed as limiting the scope of the invention.

[0021] In the description of the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0022] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0023] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0024] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0025] The following is combined Figure 1 The present invention describes the turbine rear support plate of the oil-gas matching form.

[0026] like Figure 1 As shown, in an embodiment of the present invention, the turbine rear support plate of the oil-gas matching type includes a support plate body 1, the support plate body 1 has a cavity, a portion of the support plate body 1 is recessed into the cavity, so that the recessed area forms a return flow zone 20, and the cavity is used to inject cooling gas and fuel into the return flow zone 20.

[0027] Specifically, in existing technology, after fuel is burned in the main combustion chamber, it produces high-temperature and high-pressure gas. After the gas drives the turbine to do work, it still has a high temperature. Because this part of the gas has already participated in the combustion reaction, the oxygen content in the gas is low and cannot meet the combustion requirements; at the same time, the high temperature of the gas will cause the turbine's rear support plate to overheat severely.

[0028] In this embodiment, to prevent the support plate body 1 from overheating, cooling gas is injected into the cavity of the support plate body 1. The cooling gas has a low temperature and high pressure, which can effectively cool the support plate body 1. At the same time, the cooling gas is an unburned gas with a high oxygen content. After cooling the support plate body 1, the cooling gas is ejected from the support plate body 1 to participate in combustion.

[0029] The support plate body 1 is recessed into the cavity to form a reflux zone 20. Fuel is sprayed out from the cavity of the support plate body 1. Under the action of high temperature combustion gas, the fuel evaporates rapidly and mixes with the cooling gas. It is ignited and burned in the reflux zone 20, which can greatly reduce the difficulty of organizing combustion under low oxygen content in the inflow condition, and will not have a significant adverse effect on the cooling of the support plate body 1 and the organization of combustion within it.

[0030] The turbine rear support plate with oil-gas matching provided in this embodiment of the invention can significantly improve the ignition speed and combustion stability of the recirculation zone of the support plate body by introducing high oxygen content cooling gas after the core fan. The oil-gas matching form meets the requirements of the wide-range afterburner of the new generation of aero engines for low oxygen content incoming flow combustion.

[0031] like Figure 1 As shown, in an embodiment of the present invention, the support plate body 1 includes a first plate 11 and a second plate 12. The first plate 11 and the second plate 12 are arranged perpendicularly to form a reflux zone 20. The first plate 11 is provided with a first through hole 111, and the second plate 12 is provided with a second through hole 121. Both the first through hole 111 and the second through hole 121 are connected to the cavity. The first through hole 111 is used to inject fuel into the reflux zone 20, and the second through hole 121 is used to inject cooling gas into the reflux zone 20.

[0032] Specifically, the recirculation zone 20 is formed on the outside of the support plate body 1. Cooling gas first enters the cavity of the support plate body 1 to cool it, causing the temperature of the cooling gas to rise. Then, the cooling gas is injected into the recirculation zone 20 through the second through-hole 121. Fuel is injected into the recirculation zone 20 through the first through-hole 111. The cooling gas, fuel, and the high-temperature combustion gas after work are mixed and ignited in the recirculation zone 20.

[0033] Furthermore, such as Figure 1 As shown, the diameter of the second through hole 121 should be as small as possible to reduce the speed at which cooling gas flows out of the cavity and ensure the cooling effect of the support plate body 1. At the same time, the number of second through holes 121 is much greater than the number of first through holes 111 to ensure sufficient oxygen supply during fuel combustion and to ensure ignition and combustion effects.

[0034] In an embodiment of the present invention, at least one of the first through hole 111 and the second through hole 121 is inclined toward the other.

[0035] Specifically, the first through hole 111 can be inclined toward the second through hole 121 to ensure that the fuel can be fully atomized, evaporated and fully mixed with the cooling gas before the return zone 20, so as to promote the complete combustion of the fuel; optionally, the second through hole 121 can also be inclined toward the first through hole 111 to form a gas film and ensure that the oxygen content of the return zone 20 meets the combustion requirements of the fuel; optionally, the first through hole 111 and the second through hole 121 can also be inclined toward each other at the same time.

[0036] like Figure 1 As shown, in an embodiment of the present invention, the first plate 11 and the second plate 12 are configured as bent portions, and the support plate body 1 has a pair of bent portions. The pair of bent portions are symmetrically arranged about the axis of the support plate body 1, so that the support plate body 1 has two recirculation zones 20. Fuel and cooling gas can be ignited and burned in the two recirculation zones 20 on both sides of the support plate body 1, ensuring that the fuel is fully burned in the afterburner.

[0037] like Figure 1 As shown, in an embodiment of the present invention, the support plate body 1 further includes a first bending plate 13 and a second bending plate 14. The first bending plate 13 is connected to a pair of first plates 11, and the second bending plate 14 is connected to a pair of second plates 12. The space between the first bending plate 13, the pair of bending portions and the second bending plate 14 forms a cavity.

[0038] In this embodiment, the cross-sectional shape of the support plate body 1 is similar to that of a fish, the bend of the first bending plate 13 is a pointed tip, and the first bending plate 13 is streamlined to reduce drag during flight. Along the extension direction of the cavity, that is, along the extension direction from the first bending plate 13 to the second bending plate 14, the distance between the opposite sides of the second bending plate 14 gradually increases, so that a recirculation zone 20 is formed between the first bending plate 13 and the second bending plate 14, ensuring stable combustion of fuel and cooling gas in the recirculation zone 20.

[0039] like Figure 1 As shown, in an embodiment of the present invention, the cavity includes a first cavity 15, a second cavity 16 and a third cavity 17, which are connected in sequence. Fuel is sprayed out from the first cavity 15 and cooling gas is sprayed out from the second cavity 16.

[0040] Specifically, since the shapes of the first bending plate 13, the first plate 11, the second plate 12, and the second bending plate 14 are different, the shape of the cavity of the support plate body 1 formed by the first bending plate 13, the first plate 11, the second plate 12, and the second bending plate 14 is also irregular. In this embodiment, fuel is injected outward from the first cavity 15, and cooling gas is injected outward from the second cavity 16. The fuel and cooling gas meet and mix after being injected outside the support plate body 1, which minimizes the flow path of the fuel and cooling gas. This facilitates further atomization and mixing of the fuel by the cooling gas and prevents the high-oxygen-content cooling gas from being diluted by the external flow, thus improving combustion efficiency.

[0041] like Figure 1 As shown, in an embodiment of the present invention, the turbine rear support plate of the oil-gas matching type further includes a pair of fuel lines disposed within the first cavity 15. Each fuel line is used to inject fuel through a first through hole 111 on a first plate 11. Specifically, each fuel line includes a main fuel line 18 and multiple fuel branch lines. The main fuel line 18 is disposed within the first cavity 15, and both ends of each fuel branch line are connected to the main fuel line 18 and a first through hole 111, respectively. Fuel flows from the main fuel line 18 to each fuel branch line and is then injected through each first through hole 111. Cooling gas is injected through each second through hole 121, and the cooling gas mixes and burns with the fuel in the recirculation zone 20.

[0042] The turbine rear support plate with oil-gas matching provided in this embodiment of the invention introduces cooling gas to organize combustion in the low-oxygen-content inlet flow, solving the problem of difficult combustion in the low-oxygen-content inlet flow; the cooling gas can effectively cool down the turbine rear support plate without having a significant impact on it; by supplying oil through the first plate and gas through the second plate, the oil-gas matching form has little impact on fuel atomization, evaporation, and mixing, and can fully and efficiently mix fuel and cooling gas in the recirculation zone, ensuring complete combustion of fuel in the recirculation zone, which is beneficial to the organized combustion in the inlet and ensures efficient combustion in the afterburner.

[0043] This invention also provides an aero-engine, including a main combustion chamber, a turbine, a cooler, and an afterburner. The main combustion chamber generates high-temperature, high-pressure combustion gas, which drives the turbine to rotate. The turbine has a turbine rear support plate in the form of an oil-gas matching system. The cooler is connected to the cavity of the turbine rear support plate, and the afterburner is located downstream of the turbine rear support plate.

[0044] Specifically, after the fuel burns in the main combustion chamber, it produces high-temperature, high-pressure combustion gas. This gas drives the turbine to perform work, but it still maintains a high temperature. Because this portion of the gas has already participated in the combustion reaction, its oxygen content is low and cannot meet the combustion requirements. The turbine rear support plate includes a support plate body 1, which has a cavity. A cooler is used to inject cooling gas into the cavity of the support plate body 1. This cooling gas has a low temperature and high pressure, effectively cooling the support plate body 1. Simultaneously, the cooling gas is an unburned gas with a high oxygen content. After cooling the support plate body 1, the cooling gas is ejected from the support plate body 1 to participate in combustion.

[0045] The support plate body 1 is recessed into the cavity to form a reflux zone 20. Fuel is sprayed out from the cavity of the support plate body 1. Under the action of high-temperature combustion gas, the fuel evaporates rapidly and mixes with the cooling gas. It is ignited and burned in the reflux zone 20 and then fully burned in the afterburner.

[0046] The aero-engine provided in this embodiment of the invention, by setting a turbine rear support plate with oil-gas matching, introduces high oxygen content cooling gas after the core fan, which can effectively improve the ignition speed and combustion stability of the recirculation zone of the support plate body. The oil-gas matching form meets the requirements of the wide-range afterburner of the new generation of aero-engines for low oxygen content incoming flow combustion.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A turbine rear support plate of oil-gas matching type, characterized in that, Includes a support plate body, the support plate body having a cavity, a portion of the support plate body being recessed into the cavity to form a reflux zone, the cavity being used to inject cooling gas and fuel into the reflux zone; The support plate body includes a first plate and a second plate. The first plate and the second plate are arranged perpendicularly to form the reflux zone. The first plate is provided with a first through hole, and the second plate is provided with a second through hole. Both the first through hole and the second through hole are connected to the cavity. The first through hole is used to inject fuel into the recirculation zone, and the second through hole is used to inject cooling gas into the recirculation zone.

2. The turbine rear support plate of the oil-gas matching type according to claim 1, characterized in that, At least one of the first through hole and the second through hole is inclined toward the other.

3. The turbine rear support plate of the oil-gas matching type according to claim 1, characterized in that, The first plate and the second plate are configured as bent portions, and the support plate body includes a pair of the bent portions. The pair of bent portions are symmetrically arranged about the axis of the support plate body so that the support plate body forms two recirculation zones.

4. The turbine rear support plate of the oil-gas matching type according to claim 3, characterized in that, The support plate body also includes a first bending plate and a second bending plate. The first bending plate is connected to a pair of first plates, and the second bending plate is connected to a pair of second plates. The space between the first bending plate, the pair of bending portions, and the second bending plate forms the cavity.

5. The turbine rear support plate of the oil-gas matching type according to claim 4, characterized in that, The cavity includes a first cavity, a second cavity, and a third cavity, wherein the first cavity, the second cavity, and the third cavity are connected in sequence. The fuel is ejected from the first chamber, and the cooling gas is ejected from the second chamber.

6. The turbine rear support plate of the oil-gas matching type according to claim 5, characterized in that, It also includes a pair of fuel lines, which are disposed in the first cavity, and each of the fuel lines is used to spray fuel from a first through hole on the first plate. Each of the fuel lines includes a main fuel line and multiple branch fuel lines. The main fuel line is disposed in the first cavity, and both ends of each branch fuel line are respectively connected to the main fuel line and a first through hole.

7. The turbine rear support plate of the oil-gas matching type according to claim 4, characterized in that, The first bent plate has a pointed bend and is streamlined.

8. The turbine rear support plate of the oil-gas matching type according to claim 4, characterized in that, Along the extending direction of the cavity, the distance between the opposite sides of the second bent plate gradually increases.

9. An aircraft engine, characterized in that, Includes the main combustion chamber, turbine, air conditioner, and afterburner; The main combustion chamber is used to generate high-temperature and high-pressure gas, which drives the turbine to rotate. The turbine has a turbine rear support plate in the form of oil-gas matching as described in any one of claims 1-8. The air cooler is connected to the cavity of the turbine rear support plate, and the afterburner is located downstream of the turbine rear support plate.

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