Variable-cross-section special-shaped gas exhaust pipe, liquid rocket engine and liquid rocket

Abstract

The utility model provides a variable-cross-section special-shaped gas exhaust pipe, a liquid rocket engine and a liquid rocket. The variable-cross-section special-shaped gas exhaust pipe comprises an inlet flange arranged at an inlet, an outlet flange arranged at an outlet and a barrel section arranged between the inlet flange and the outlet flange. The inlet and the outlet are eccentrically arranged; the inlet flange is connected with a turbine, and the outlet flange is connected with the thrust chamber gas collecting ring; high-temperature fuel gas enters from the inlet, flows out from the outlet, enters the thrust chamber gas collection ring and then is introduced into the spray pipe extension section. The exhaust pipe is connected between the turbine and the thrust chamber gas collecting ring, the eccentric layout design is adopted, and the problems that in the structural layout of an existing liquid rocket engine, the center distance between a turbine pump and a thrust chamber is large, the radial envelope of the whole machine is large, and the distance between a swing hose and the swing center is large are solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of engine exhaust pipe of carrier rocket, concretely relates to a variable cross section special-shaped gas exhaust pipe, liquid rocket engine and liquid rocket. BACKGROUND

[0002] The turbine exhaust pipe is an important component of the liquid rocket engine, when the engine works, the high-temperature gas generated by the generator is discharged by the exhaust pipe after working in the turbine, or is introduced into the nozzle extension section of the thrust chamber.

[0003] The existing turbine exhaust pipe is designed in a cylindrical shape and is arranged concentrically, the turbine pump has a large center distance from the thrust chamber, which is not conducive to compact layout and has a large radial envelope. SUMMARY

[0004] Therefore, the utility model embodiment aims to provide a variable cross section special-shaped gas exhaust pipe and carrier rocket to solve the above technical problems.

[0005] To achieve the above purpose, in the first aspect, the utility model embodiment provides a variable cross section special-shaped gas exhaust pipe, which comprises an inlet flange arranged at an inlet, an outlet flange arranged at an outlet, and a cylinder segment arranged between the inlet flange and the outlet flange.

[0006] The inlet and the outlet are arranged eccentrically.

[0007] The inlet flange is used for connecting with the turbine, and the outlet flange is used for connecting with the thrust chamber gas collecting ring.

[0008] The high-temperature gas enters the inlet, flows out of the outlet, enters the thrust chamber gas collecting ring, and then is introduced into the nozzle extension section.

[0009] In some possible implementation manners, the cylinder segment is a variable cross section cylinder segment, and the cross section area of the inlet of the cylinder segment is larger than the cross section area of the outlet of the cylinder segment.

[0010] In some possible implementation manners, the cross section area of the inlet is 1.5 to 2 times the cross section area of the outlet. In some possible implementation manners, the variable cross section cylinder segment is designed in a special shape, and the profile of the variable cross section cylinder segment expands outward along the thrust chamber expansion section, so that the inlet flange to the outlet flange is smoothly transitioned.

[0011] In some possible implementation manners, the variable cross-section special-shaped gas exhaust pipe further comprises a corrugated hose arranged between the cylinder segment and the outlet flange; and two ends of the corrugated hose are connected with the cylinder segment and the outlet flange respectively.

[0012] In some possible implementation manners, the sealing structure between the inlet flange and the turbine is a tenon and slot structure, and a graphite gasket is used as a sealing gasket, and / or the sealing structure between the outlet flange and the thrust chamber gas collecting ring is a tenon and slot structure, and a graphite gasket is used as a sealing gasket.

[0013] In some possible implementation manners, the inlet flange is provided with axial connection lugs, and the number of the axial connection lugs is greater than or equal to two, which are used to constrain the axial positions of the turbine and the variable cross-section special-shaped gas exhaust pipe on the pump support of the engine.

[0014] In some possible implementation manners, the inlet flange is provided with at least one radial connection lug, which is used to constrain the radial positions of the turbine and the variable cross-section special-shaped gas exhaust pipe on the pump support of the engine.

[0015] In a second aspect, the utility model also provides a liquid rocket engine, the liquid rocket engine includes the variable cross-section special-shaped gas exhaust pipe of first aspect.

[0016] In a third aspect, the utility model also provides a liquid rocket, the liquid rocket includes the liquid engine of second aspect.

[0017] The utility model embodiment has the following beneficial effects:

[0018] The variable cross-section special-shaped gas exhaust pipe is used for connecting the turbine and the thrust chamber gas collecting ring, the variable cross-section special-shaped gas exhaust pipe adopts eccentric layout design, so that the problem that the turbine pump and the thrust chamber center distance are large in the structure layout of the existing rocket engine, the whole machine radial envelope is large, and the swing hose distance from the swing center is large is solved.

[0019] The cylinder segment adopts special-shaped design, can effectively reduce the exhaust pipe height, improves the problem that the engine whole machine axial height is high, is favorable for rocket pressurization delivery pipeline layout, and is further favorable for rocket section height reduction.

[0020] The utility model embodiment adopts the design of the corrugated compensation pipe, can compensate axial and radial assembly deviation, and also can compensate the axial and radial deformation generated by the high-temperature gas acting on the exhaust pipe in the engine operation. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0022] Figure 1 is a structural schematic diagram of a variable cross-section special-shaped gas exhaust pipe according to an embodiment of the present application;

[0023] Figure 2 is a side view of a variable cross-section special-shaped gas exhaust pipe according to an embodiment of the present application.

[0024] Explanation of reference numerals:

[0025] 1, inlet; 2, outlet; 3, corrugated hose; 4, inlet flange; 5, outlet flange; 6, cylinder segment; 7, axial connection lug; 8, radial connection lug. DETAILED DESCRIPTION

[0026] The features and exemplary embodiments of each aspect of the present application will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to those skilled in the art that the present application can be practiced without some of these specific details. The description of the embodiments is merely intended to provide a better understanding of the present application by showing examples of the present application. In the drawings and the following description, at least some well-known structures and techniques are not shown in order to avoid unnecessary obscuring of the present application; and, for clarity, the dimensions of some structures can be exaggerated. In addition, the features, structures or characteristics described below can be combined in any suitable manner in one or more embodiments.

[0027] The embodiment of the present application provides an exhaust pipe for connecting a turbine and a thrust chamber gas collecting ring, the exhaust pipe adopts an eccentric layout design, so as to solve the problems of a large center distance between a turbine pump and a thrust chamber, a large radial envelope of a whole machine and a large distance between a swing hose and a swing center in the structure layout of an existing rocket engine; the special-shaped design is adopted, so as to effectively reduce the height of the exhaust pipe, improve the problem of a high axial height of the whole engine, and be beneficial to the layout of a rocket pressurization delivery pipeline, and then be beneficial to the reduction of the height of a rocket section; the corrugated compensation pipe design is adopted, so as to compensate for the axial and radial assembly deviations, and also compensate for the axial and radial deformations of the exhaust pipe caused by the high-temperature gas in the engine.

[0028] Embodiment one

[0029] Figure 1It is a structural schematic view of a variable cross-section special-shaped gas exhaust pipe according to an embodiment of the present application, as shown in Figure 1 The variable cross-section special-shaped gas exhaust pipe comprises: an inlet flange 4 arranged at an inlet 1, an outlet flange 5 arranged at an outlet 2, and a cylinder segment 6 arranged between the inlet flange 4 and the outlet flange 5; the inlet 1 and the outlet 2 are arranged in an eccentric manner; the inlet flange 4 is used to be connected with a turbine, and the outlet flange 5 is used to be connected with a thrust chamber gas collecting ring; high-temperature gas enters from the inlet 1, flows out from the outlet 2, enters the thrust chamber gas collecting ring, and then enters an extension section of a nozzle.

[0030] In the embodiment, the turbine exhaust entering the extension section of the nozzle has three main effects: first, it forms a gas film cooling protection for the extension section of the nozzle, improves the working reliability of the extension section of the nozzle, reduces the temperature resistance requirement of the material of the extension section of the nozzle, and reduces the cost and weight; second, the turbine rich exhaust increases the gas momentum at the outlet 2 of the nozzle, and generates additional thrust; third, the turbine rich exhaust entering the extension section of the nozzle in the thrust chamber can be combusted again, can increase the specific impulse of the engine, and improves the overall specific impulse of the engine.

[0031] The exhaust pipe according to the embodiment of the present application is connected between the turbine and the thrust chamber gas collecting ring, and is designed in an eccentric manner, thereby solving the problems that the turbine pump and the thrust chamber have a large center distance in the structural layout of the existing rocket engine, the overall radial envelope of the engine is large, and the swing hose has a large distance from the swing center.

[0032] Figure 2 It is a side view of a variable cross-section special-shaped gas exhaust pipe according to an embodiment of the present application, as shown in Figure 2 In some embodiments, the cylinder segment 6 is an eccentric variable cross-section cylinder segment 6, and the inlet cross-sectional area of the cylinder segment 6 is larger than the outlet cross-sectional area of the cylinder segment 6. In some embodiments, the inlet cross-sectional area is 1.5 to 2 times the outlet cross-sectional area, and the inlet diameter of the cylinder segment 6 is about 1.2 to 1.6 times the outlet diameter of the cylinder segment 6.

[0033] The variable cross-section cylinder segment 6 according to the embodiment adopts an eccentric layout, the inlet 1 is close to the thrust chamber, the profile expands outward along with the thrust chamber expansion section, the center distance between the turbine pump and the thrust chamber can be reduced, the radial envelope of the engine is reduced, the structural layout of the engine pump before swing is more compact, the distance of the swing hose from the swing center can be reduced, and the design difficulty of the swing hose is reduced.

[0034] The swing hose is another part of the engine, and is arranged at the inlet of the oxidant and the fuel of the engine. Although it is not at the position of the exhaust pipe, since the inlet of the exhaust pipe is the turbine outlet of the turbine pump, the closer the variable cross-section cylinder segment to the thrust chamber, the closer the turbine pump to the thrust chamber, and the distance of the corresponding swing hose from the center of the thrust chamber is smaller, so that the distance of the swing hose from the swing center can be reduced, and the design difficulty of the swing hose is reduced.

[0035] The eccentric variable cross-section cylinder segment 6 is designed as a special shape, and the profile of the eccentric variable cross-section cylinder segment 6 expands outward along with the expansion of the thrust chamber, so as to realize smooth transition from the inlet flange 4 to the outlet flange 5. The special shape has two aspects, one is that the inlet and outlet of the cylinder segment 6 are not coaxial, and the other is that the inlet has a large diameter and the outlet has a small diameter, and the area of the inlet to the area of the outlet is a variable cross-section transition, so the entire exhaust pipe is neither a regular solid of revolution such as a cylinder nor a cone, but a special profile that smoothly and gradually transitions from the inlet (large area) to the outlet (small area). In this embodiment, the variable cross-section cylinder segment 6 is designed as a special shape, realizes variable diameter and eccentric smooth transition from the inlet 1 to the outlet 2, and can reduce the axial height of the variable cross-section cylinder segment 6 to the greatest extent, thereby effectively reducing the overall height of the exhaust pipe and reducing the axial height of the engine, which is conducive to the layout of the rocket conveying pipeline.

[0036] As shown in Figure 1 and Figure 2 , in some embodiments, the variable cross-section special gas exhaust pipe further comprises a corrugated hose 3 arranged between the cylinder segment 6 and the outlet flange 5, and the two ends of the corrugated hose 3 are connected with the cylinder segment 6 and the outlet flange 5 respectively.

[0037] The corrugated compensating pipe in this embodiment can compensate for the axial and radial assembly deviations in the assembly process of the turbine pump, and can also compensate for the axial and radial deformation of the exhaust pipe caused by the high-temperature gas acting on the exhaust pipe during engine operation.

[0038] In some embodiments, the sealing structure between the inlet flange 4 and the turbine is a tenon and groove structure, and the sealing gasket is a graphite gasket. The sealing structure between the outlet flange 5 and the thrust chamber gas collecting ring is a tenon and groove structure, and the sealing gasket is a graphite gasket. The tenon and groove structure and the sealing gasket are used to realize reliable sealing of the connection parts of the inlet flange 4 and the turbine, and the outlet flange 5 and the thrust chamber gas collecting ring.

[0039] As shown in Figure 1 , in some embodiments, the inlet flange 4 is provided with an axial connection lug 7, and the number of the axial connection lug 7 is greater than or equal to two, which is used to constrain the axial position of the turbine and the variable cross-section special gas exhaust pipe on the pump support of the engine.

[0040] The inlet flange 4 is provided with at least one radial connection lug 8, which is used to constrain the radial position of the turbine and the variable cross-section special gas exhaust pipe on the pump support of the engine.

[0041] In the embodiment, two axial connecting lugs 7 and one radial connecting lug 8 are arranged on the inlet flange 4, so that the turbine pump and the exhaust pipe can be connected and fixed on the engine pump support as a whole, the axial position is constrained by the connecting lugs, and the radial position is constrained by the connecting lugs.

[0042] Embodiment two

[0043] The utility model discloses still provide a kind of liquid rocket engine, the liquid rocket engine uses the variable cross-section special-shaped gas exhaust pipe of embodiment one.

[0044] Embodiment three

[0045] The utility model discloses still provide a kind of liquid rocket, the liquid rocket engine uses the liquid rocket engine of embodiment two.

[0046] In the prior art, the rocket engine, which introduces turbine exhaust into the extension section of the nozzle, has a large center distance between the turbine pump and the thrust chamber in the structural layout, and has a large radial envelope of the whole machine. The exhaust pipe of the embodiment has a variable cross-section special-shaped structure with eccentric layout of the inlet 1 and the outlet 2, which can reduce the center distance between the turbine pump and the thrust chamber, reduce the envelope of the engine, make the structural layout of the whole engine more compact, be conducive to the layout of the rocket pressurization delivery pipeline, and further be conducive to reducing the height and weight of the rocket section.

[0047] The exhaust pipe in the embodiment includes an interface for mounting and fixing the turbine pump, and the turbine pump does not need to be provided with an additional interface for external mounting and fixing, so that the turbine pump products of the rocket primary and secondary engines can be universalized.

[0048] In the description of the embodiments of the utility model, it should be explained that the directions or position relationships indicated by the terms "up, down, inner and outer" are based on the directions or position relationships shown in the drawings, and are only for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the indicated devices or elements must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the utility model. In addition, the terms "first, second or third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0049] In the embodiments of the utility model, unless otherwise explicitly specified and limited, the terms "mounting, connecting and connecting" should be understood broadly, for example: it can be fixed connection, detachable connection or integral connection; it can also be mechanical connection, electrical connection or direct connection, and can also be indirectly connected through an intermediate medium, or the communication between two elements. For ordinary skilled persons in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0050] Although the present application has been described with reference to the preferred embodiments, various modifications can be made to the application without departing from the scope thereof. In particular, individual features mentioned in each of the embodiments can be permissibly combined with each other in any way, provided that there is no structural conflict. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A variable cross-section irregular-shaped gas exhaust pipe, characterized in that, The variable cross-section special-shaped gas exhaust pipe includes: an inlet flange (4) provided at the inlet (1), an outlet flange (5) provided at the outlet (2), and a cylindrical section (6) provided between the inlet flange (4) and the outlet flange (5). The inlet (1) and the outlet (2) are arranged eccentrically; The inlet flange (4) is used to connect to the turbine, and the outlet flange (5) is used to connect to the thrust chamber gas collecting ring; The gas enters from the inlet (1), flows out from the outlet (2), enters the gas collection ring of the thrust chamber, and is then introduced into the nozzle extension section.

2. The variable cross-section irregular-shaped gas exhaust pipe according to claim 1, characterized in that, The cylindrical section (6) is a variable cross-section cylindrical section (6), and the inlet cross-sectional area of ​​the cylindrical section (6) is greater than the outlet cross-sectional area of ​​the cylindrical section (6).

3. A variable cross-section irregular-shaped gas exhaust pipe according to claim 2, characterized in that, The inlet cross-sectional area is 1.5 to 2 times the outlet cross-sectional area.

4. A variable cross-section irregular-shaped gas exhaust pipe according to claim 2, characterized in that, The variable cross-section cylindrical section (6) is an irregular design. The profile of the variable cross-section cylindrical section (6) expands outward with the thrust chamber expansion section to achieve a smooth transition of diameter change and eccentricity from the inlet (1) to the outlet (2).

5. A variable cross-section irregular-shaped gas exhaust pipe according to claim 1, characterized in that, The variable cross-section special-shaped gas exhaust pipe also includes a corrugated hose (3), which is disposed between the cylindrical section (6) and the outlet flange (5); the two ends of the corrugated hose (3) are respectively connected to the cylindrical section (6) and the outlet flange (5).

6. A variable cross-section irregular-shaped gas exhaust pipe according to claim 1, characterized in that, The sealing structure between the inlet flange (4) and the turbine is a tenon and groove structure, and / or the sealing structure between the outlet flange (5) and the thrust chamber gas collecting ring is a tenon and groove structure.

7. A variable cross-section irregular-shaped gas exhaust pipe according to claim 1, characterized in that, The inlet flange (4) is provided with an axial connecting lug (7), and the number of the axial connecting lugs (7) is greater than or equal to two, which are used to constrain the axial position of the turbine and the variable cross-section special-shaped gas exhaust pipe on the pump support of the engine.

8. A variable cross-section irregular-shaped gas exhaust pipe according to claim 1, characterized in that, At least one radial connecting lug (8) is provided on the inlet flange (4) to constrain the radial position of the turbine and the variable cross-section gas exhaust pipe on the pump support of the engine.

9. A liquid rocket engine, characterized in that, The liquid rocket engine includes a variable cross-section irregular gas exhaust pipe as described in any one of claims 1-8.

10. A liquid rocket, characterized in that, The liquid rocket engine includes the liquid rocket engine described in claim 9.

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