A component for increasing the thrust after the turbine of an aero-turbine engine

Abstract

The application belongs to the technical field of non-variable engine component design, and specifically relates to a component for increasing the thrust after the turbine of an aero-turbine engine. In the design, a component composed of a heat shield, an oil inlet pipe, an injector, and a flow regulating piece is used to replace the existing fuel injection rod. The bypass air is introduced to cool the component, avoiding damage to the component, and the flow rate of the bypass air introduced can be controlled to change the amount of air mixed with the fuel, so as to adjust the position of the flame front. It is convenient and fast, can effectively reduce the combustion pulsation generated in the thrust-increasing component, and overcome the problems of incomplete combustion and flameout.

Description

Technical Field

[0001] The present application belongs to the technical field of non-variable volume engine component design, and specifically relates to a turbine thrust increasing component for an aviation turbine engine. Background Art

[0002] The thrust increasing component of the turbine of an aviation turbine engine mainly comprises an outer casing 1, a confluence ring 2 arranged in the outer casing 1, an inner cone 3 arranged in the confluence ring 2, and a support plate 4 supported circumferentially between the confluence ring 2 and the inner cone 3, wherein the outer casing 1 and the confluence ring 2 constitute an outer culvert, and the confluence ring 2 and the inner cone 3 constitute an inner culvert. In addition, a fuel injection rod 12 is designed to penetrate the outer casing 1 and the confluence ring 2 and extend into the inner culvert, and fuel is injected into the inner culvert by the fuel injection rod 12 to mix with air, cooperate with a stabilizer, and ignite by an ignition nozzle or by a jet ignition method, so as to organize combustion in the thrust increasing component to increase the thrust of the aviation turbine engine.

[0003] The energy flow density in the thrust-increasing component of the turbine of an aviation turbine engine is large and the flow speed is fast. The flame burns in an inappropriate position, which is very likely to cause combustion pulsation, incomplete combustion and flameout. Under the existing structure, it is difficult to adaptively adjust the position of the flame front when oscillating combustion occurs. To adjust the position of the flame front, it is necessary to redesign the structure, which is time-consuming and laborious. In addition, there is a lack of effective cooling means for the injection rod 12. The injection rod 12 is subjected to high-temperature radiation and is very likely to be ablated, cracked and coked.

[0004] This application is proposed in view of the above-mentioned technical defects.

[0005] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention

[0006] The purpose of the present application is to provide a turbine thrust increasing component for an aviation turbine engine to overcome or alleviate at least one of the known technical deficiencies.

[0007] The technical solution of this application is:

[0008] A turbine thrust increasing component for an aviation turbine engine, comprising:

[0009] Outer receiver;

[0010] The confluence ring is arranged in the outer casing and forms an outer culvert with the outer casing;

[0011] Inner cone, arranged inside the confluence ring, forming an inner cavity with the confluence ring;

[0012] Multiple struts, circumferentially supporting between the outer casing and the confluence ring;

[0013] Heat shield, one end is sealed and the other end is open. Among them, the open end is connected to the inner side of the outer casing, penetrates through the side wall of the confluence ring, the leading edge side wall has an air scoop opening, both side walls have air outlet holes and are formed with a pair of positioning blocks; the air scoop opening is located in the outer flow path; the two air outlet holes are located in the inner flow path; the two pairs of positioning blocks have guide grooves;

[0014] Fuel inlet pipe, the outlet end extends into the heat shield and penetrates through the outer casing;

[0015] Two fuel injectors, connected to the fuel inlet pipe; each fuel injector corresponds to extending out from one of the air outlet holes, and has a large clearance fit with the corresponding air outlet hole;

[0016] Two flow regulating vanes, the two side edges of each flow regulating vane are respectively snapped into a pair of guide grooves, and are attached to the side wall of the corresponding side of the heat shield, and can slide to block and adjust the effective flow area of the air outlet hole on the corresponding side of the heat shield.

[0017] According to at least one embodiment of the present application, in the above-mentioned component for increasing the turbine rear thrust of an aero-turbine engine, the outer shape of the heat shield adopts a streamlined design.

[0018] According to at least one embodiment of the present application, in the above-mentioned component for increasing the turbine rear thrust of an aero-turbine engine, the side wall of the open end of the heat shield has a first connecting edge;

[0019] The side wall of the inlet end of the fuel inlet pipe has a second connecting edge;

[0020] The first connecting edge together with the second connecting edge are connected to the outer casing by bolt fasteners.

[0021] According to at least one embodiment of the present application, in the above-mentioned component for increasing the turbine rear thrust of an aero-turbine engine, one end edge of the two flow regulating vanes has an outward flanging, and the other end edge faces the corresponding air outlet hole, and a notch with a shape adapted to the outer shape of the corresponding fuel injector is provided on this end edge.

[0022] According to at least one embodiment of the present application, in the above-mentioned component for increasing the turbine rear thrust of an aero-turbine engine, it further includes:

[0023] Two fixing blocks, welded inside the heat shield, clamping the fuel inlet pipe.

[0024] According to at least one embodiment of the present application, in the above-mentioned component for increasing the turbine rear thrust of an aero-turbine engine, the two flow regulating vanes are provided with strip holes;

[0025] The after-turbine thrust increasing component of the aero-turbine engine further includes:

[0026] A bracket, welded inside the heat shield and embedded with nuts;

[0027] Two screws, each screw passing through a strip hole and the corresponding side wall of the heat shield, and screwed into the nut to fasten the corresponding flow regulating piece. When loosened, the corresponding flow regulating piece can slide.

[0028] The present application has at least the following beneficial technical effects:

[0029] Provide an after-turbine thrust increasing component of an aero-turbine engine, in which a component composed of a heat shield, an inlet oil pipe, an injector nozzle, and a flow regulating piece is designed to replace the existing injector rod, introduce bypass air to cool the component, avoid damage to the component, and can control the flow rate of the introduced bypass air, change the amount of air mixed with fuel, and achieve the adjustment of the flame front position, which is convenient and fast, and can easily reduce the combustion pulsation generated in the thrust increasing component, and overcome the problems of incomplete combustion and flameout. Description of the Drawings

[0030] Figure 1 is a schematic diagram of the after-turbine thrust increasing component of the aero-turbine engine;

[0031] Figure 2 is a partial structural schematic diagram of the after-turbine thrust increasing component of the aero-turbine engine;

[0032] Figure 3 is Figure 2 a side sectional view of

[0033] Figure 4 is Figure 2 a partial sectional view of

[0034] Wherein:

[0035] 1 - Outer casing; 2 - Confluence ring; 3 - Inner cone; 4 - Support plate; 5 - Heat shield; 6 - Inlet oil pipe; 7 - Injector nozzle; 8 - Flow regulating piece; 9 - Fixed block; 10 - Bracket; 11 - Screw; 12 - Injector rod.

[0036] For better illustration of this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation of this patent. Detailed Embodiment

[0037] To make the technical solutions and their advantages of this application clearer, the following will further clearly and completely describe the technical solutions of this application in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments and the technical features in the embodiments in this application can be combined with each other to obtain new embodiments.

[0038] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The terms indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to represent relative directions or position relationships, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the object being described changes, its relative position relationship may also change accordingly. Therefore, it cannot be understood as a limitation to this application. The terms "first", "second", "third", and similar terms used in the description of this application are only for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar terms such as "a", "one", or "the" used in the description of this application should not be understood as an absolute limitation on the quantity, but should be understood as having at least one. The terms "including" or "comprising" and similar terms used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0039] In addition, it should also be noted that unless otherwise clearly specified and limited, the similar terms such as "installed", "connected", and "coupled" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and can also be the communication inside two elements. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0040] Tests have proven that in the component for increasing the thrust after the turbine of an aero-turbine engine, by adjusting the amount of air mixed with fuel, the ignition time of the gas can be changed, and the adjustment of the flame front position can be achieved. Based on this, this application provides a component for increasing the thrust after the turbine of an aero-turbine engine. The following will Figures 1 to 4 make a further detailed description of this application.

[0041] An after-turbine thrust increasing component for an aero-turbine engine, comprising:

[0042] An outer casing 1;

[0043] A confluence ring 2, disposed within the outer casing 1, forming an outer flow path between it and the outer casing 1;

[0044] An inner cone 3, disposed within the confluence ring 2, forming an inner flow path between it and the confluence ring 2;

[0045] A plurality of struts 4, circumferentially supported between the outer casing 1 and the confluence ring 2;

[0046] A heat shield 5, one end of which is sealed and the other end is open. The open end is connected to the inner side of the outer casing 1, penetrates through the side wall of the confluence ring 2, has an air scoop opening at the leading edge side wall, has air outlet holes on both side walls, and is formed with a pair of positioning blocks; the air scoop opening is located in the outer flow path; the two air outlet holes are located in the inner flow path; the two pairs of positioning blocks have guide grooves;

[0047] An oil inlet pipe 6, the outlet end of which extends into the heat shield 5 and penetrates through the outer casing 1;

[0048] Two fuel injectors 7, connected to the oil inlet pipe 6; each fuel injector 7 correspondingly extends out from one of the air outlet holes and has a large clearance fit with the corresponding air outlet hole;

[0049] Two flow regulating vanes 8, the two side edges of each flow regulating vane 8 are correspondingly clamped into a pair of guide grooves, and are attached to the side wall of the corresponding side of the heat shield 5, and can slide to block and adjust the effective flow area of the air outlet holes on the corresponding side of the heat shield 5.

[0050] For the after-turbine thrust increasing component for an aero-turbine engine disclosed in the above embodiments, those skilled in the art can understand that the component composed of the heat shield 5, the oil inlet pipe 6, the fuel injectors 7, and the flow regulating vanes 8 replaces the existing fuel injection rod 12. Multiple groups of the heat shield 5, the oil inlet pipe 6, the fuel injectors 7, and the flow regulating vanes 8 can be designed and distributed circumferentially along the thrust increasing component. When the aero-turbine engine is operating, fuel can be introduced through the inlet end of the oil inlet pipe 6, and then sprayed into the inner flow path through the fuel injectors 7, mixed with the inner flow path air in the inner flow path, and ignited and organized for combustion in cooperation with a stabilizer.

[0051] For the after-turbine thrust increasing component for an aero-turbine engine disclosed in the above embodiments, those skilled in the art can also understand that when the aero-turbine engine is operating, the outer flow path air can be efficiently introduced through the air scoop opening on the leading edge side wall of the heat shield 5, and the outer flow path air is used to effectively cool components such as the heat shield 5, the oil inlet pipe 6, and the fuel injectors 7, preventing the components from suffering high-temperature damage.

[0052] For the component for increasing the thrust after the turbine of the above-described aero-turbine engine, those skilled in the art can also understand that when the aero-turbine engine is operating, the bypass air entering the heat shield 5 flows out through the air outlet holes on the side wall. After flowing out, it will be mixed with the fuel sprayed by the fuel injector 7. By sliding the flow rate adjustment piece 8, the shielding area of the air outlet holes can be changed, that is, the effective flow area of the air outlet holes can be changed, so as to change the amount of air mixed with the fuel, and the position of the flame front can be adjusted conveniently and quickly, so as to easily eliminate the combustion pulsation generated in the thrust increasing component, and overcome the problems of incomplete combustion and flameout.

[0053] In some alternative embodiments, in the component for increasing the thrust after the turbine of the above-described aero-turbine engine, the outer shape of the heat shield 5 is designed to be streamlined to reduce the flow resistance of the air flow. Further, the trailing edge of the heat shield 5 can be designed to be a split structure to facilitate the installation of components such as the fuel inlet pipe 6 and the fuel injector 7.

[0054] In some alternative embodiments, in the component for increasing the thrust after the turbine of the above-described aero-turbine engine, the side wall at the open end of the heat shield 5 has a first connecting edge;

[0055] The side wall at the inlet end of the fuel inlet pipe 6 has a second connecting edge;

[0056] The first connecting edge together with the second connecting edge is connected to the outer casing 1 by bolt fasteners, which is stable and reliable.

[0057] In some alternative embodiments, in the component for increasing the thrust after the turbine of the above-described aero-turbine engine, one end edge of the two flow rate adjustment pieces 8 has an outward flanging, and the other end edge faces the corresponding air outlet holes. The flow rate adjustment piece 8 can be easily pushed to slide through the outward flanging, and in a shielding manner, the effective flow area of the air outlet holes can be adjusted. The air outlet holes can be designed to be strip-shaped and extend along the axial direction of the heat shield 5. The fuel injector 7 is located at the lower end, and the flow rate adjustment piece 8 is located at the upper end of the air outlet holes. A notch with a shape adapted to the outer shape of the fuel injector 7 is provided on the edge facing the air outlet holes. When the flow rate adjustment piece 8 slides down completely, it can be stuck on the fuel injector 7 to completely block the air outlet holes.

[0058] In some alternative embodiments, in the component for increasing the thrust after the turbine of the above-described aero-turbine engine, it further includes:

[0059] Two fixed clamping blocks 9, which are welded inside the heat shield 5 and clamp the fuel inlet pipe 6.

[0060] In some alternative embodiments, in the component for increasing the thrust after the turbine of the above-described aero-turbine engine, the two flow rate adjustment pieces 8 have strip-shaped holes;

[0061] The component for increasing the thrust after the turbine of the aero-turbine engine further includes:

[0062] The bracket 10 is welded inside the heat shield 5 and is embedded with nuts.

[0063] Two screws 11, each screw 11 is correspondingly arranged through a strip hole and the corresponding side wall of the heat shield 5, and is screwed into the nut to fasten the corresponding flow regulating piece 8. When loosened, the corresponding flow regulating piece 8 can slide.

[0064] In the description of the embodiments in the specification, a progressive manner is adopted. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the embodiments, reference can be made to each other.

[0065] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the protection scope of the present application.

Claims

1. A component for increasing the thrust after the turbine of an aero-turbine engine, characterized in that Comprising: Outer casing (1); Confluence ring (2), disposed within the outer casing (1), forming an outer annulus with the outer casing (1); Inner cone (3), disposed within the confluence ring (2), forming an inner annulus with the confluence ring (2); A plurality of struts (4), circumferentially supported between the outer casing (1) and the confluence ring (2); Heat shield (5), having an open end and a closed end, the open end being connected to the inner side of the outer casing (1), passing through the side wall of the confluence ring (2), the leading edge side wall having an air scoop opening, the two side walls having air outlet holes and formed with a pair of positioning blocks; the air scoop opening is located in the outer annulus; the two air outlet holes are located in the inner annulus; the two pairs of positioning blocks have guide grooves; Fuel inlet pipe (6), the outlet end extending into the heat shield (5), passing through the outer casing (1); Two fuel injectors (7), connected to the fuel inlet pipe (6); each fuel injector (7) correspondingly extends out from one air outlet hole, with a large clearance fit with the corresponding air outlet hole; Two flow regulating vanes (8), the two side edges of each flow regulating vane (8) are correspondingly snapped into a pair of guide grooves, fitting on the side wall of the corresponding side of the heat shield (5), capable of sliding to block and adjust the effective flow area of the air outlet hole on the corresponding side of the heat shield (5).

2. The component for increasing the thrust after the turbine of an aero-turbine engine according to claim 1, wherein: The outer shape of the heat shield (5) adopts a streamlined design.

3. The component for increasing the thrust after the turbine of an aero-turbine engine according to claim 1, wherein: The side wall of the open end of the heat shield (5) has a first connecting edge; The side wall of the inlet end of the fuel inlet pipe (6) has a second connecting edge; The first connecting edge together with the second connecting edge are connected to the outer casing (1) by bolt fasteners.

4. The component for increasing the thrust after the turbine of an aero-turbine engine according to claim 1, wherein: One end edge of the two flow regulating vanes (8) has an outward flanging, and the other end edge faces the corresponding air outlet hole, and a notch with a shape adapted to the outer shape of the corresponding fuel injector (7) is provided on this end edge.

5. The component for increasing the thrust after the turbine of an aero-turbine engine according to claim 1, wherein: Further comprising: Two fixing blocks (9), welded inside the heat shield (5), clamping the fuel inlet pipe (6).

6. The component for increasing the thrust after the turbine of an aero-turbine engine according to claim 1, wherein: The two flow regulating vanes (8) have strip-shaped holes; The component for increasing the thrust after the turbine of the aero-turbine engine further comprises: A bracket (10), welded inside the heat shield (5), embedded with a nut; Two screws (11), each screw (11) correspondingly passes through a strip-shaped hole and the side wall of the corresponding side of the heat shield (5), screwed into the nut, fastening the corresponding flow regulating vane (8), and when loosened, the corresponding flow regulating vane (8) can slide.

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