Oxygen-enriched turbine pump of full-flow staged combustion liquid rocket engine

Abstract

The utility model discloses an oxygen-enriched turbine pump of a full-flow staged combustion liquid rocket engine. The oxygen-enriched turbine pump comprises an oxygen pump and a turbine which are coaxially arranged on a rotating shaft in a sleeving mode. An outlet of the oxygen pump communicates with the interior of the combustor through a rotational flow generator installed at the input end of the combustor, the rotational flow generator comprises a partition plate, an outer barrel, an inner barrel and a set of rotational flow blades, and the multiple rotational flow blades are arranged between the outer barrel and the inner barrel and distributed at intervals in the circumferential direction. The partition plate is provided with a plurality of jet flow holes corresponding to the rotational flow blades. The cyclone generator is arranged, and the plurality of igniters and the plurality of injectors are arranged on one side of the combustor inner cavity of the inner barrel of the cyclone generator; liquid oxygen passes through the rotational flow generator in a full-flow manner, the movement track of the liquid oxygen is changed, so that the liquid oxygen does centrifugal movement along the circumference in the combustor, the influence of the rotating liquid oxygen fluid on the inner cylinder in the center position is relatively small, and the igniter can normally ignite.

Description

Technical Field

[0001] The utility model specifically relates to an oxygen-enriched turbopump of a full-flow staged combustion liquid rocket engine. Background Art

[0002] The oxygen-rich turbopump of a full-flow staged combustion liquid rocket engine adds low-temperature liquid oxygen and a small amount of fuel separately into a pre-combustion chamber, ignites the fuel in the pre-combustion chamber through an igniter, and the liquid oxygen after combustion vaporizes and expands to form a combustion-supporting gas, which drives the turbine to rotate. The gas is then discharged from the output end of the pre-combustion chamber and finally input into the main combustion chamber to mix with the combustible gas for combustion. The rotating turbine transmits torque to the pump wheel through the shaft, thereby increasing the pump pressure of the oxygen-rich turbopump.

[0003] The pre-combustion chamber of the prior art usually uses an electric igniter for ignition, but the temperature of liquid oxygen is below -183 degrees. When the full flow of liquid oxygen enters the pre-combustion chamber, it is easy for the electric igniter to ignite abnormally, so technical improvements in various aspects are needed. Utility Model Content

[0004] The utility model aims to overcome the above-mentioned shortcomings and provide a technical solution that can solve the above-mentioned problems.

[0005] An oxygen-enriched turbopump for a full-flow staged combustion liquid rocket engine comprises an oxygen pump and a turbine coaxially sleeved on a rotating shaft, wherein a turbine sealing device is arranged on a side of the turbine close to the oxygen pump;

[0006] The oxygen pump comprises an oxygen pump housing, an oxygen pump inducer, an oxygen pump centrifugal wheel and an oxygen pump bearing assembly; the oxygen pump housing is provided with an oxygen pump inlet and an oxygen pump outlet, the oxygen pump inducer and the oxygen pump centrifugal wheel are sleeved on a rotating shaft between the oxygen pump inlet and the oxygen pump outlet through a spline connection, and the oxygen pump bearing assembly is sleeved between the rotating shaft and the oxygen pump housing;

[0007] The turbine comprises a turbine housing, a burner, a turbine blade disk and a turbine main bearing assembly. The oxygen pump outlet is connected to the inside of the burner through a swirl generator installed at the burner input end. The swirl generator comprises a baffle, an outer cylinder, an inner cylinder and a group of swirl blades. A plurality of swirl blades are arranged between the outer cylinder and the inner cylinder and are distributed at intervals along the circumferential direction. The baffle is provided with a plurality of jet holes corresponding to the swirl blades. After the full flow of liquid oxygen passes through the jet holes, it is affected by the swirl blades to change its motion trajectory, and centrifugally moves in the burner to form a rotating fluid.

[0008] A plurality of electric igniters and a plurality of injectors are installed on one side of the burner inner cavity of the inner cylinder, and the injectors are connected to a fuel manifold, and the fuel manifold inputs a small amount of liquid fuel to the injectors;

[0009] Preferably, the output end of the oxygen pump is also connected to a liquid oxygen manifold communicating with the interior of the fuel-rich burner;

[0010] Preferably, the turbine main bearing assembly is installed between the rotating shaft and the turbine housing, and the inner ring of the turbine main bearing assembly is rotatably connected to the rotating shaft;

[0011] Preferably, the turbine blade disk is fixedly connected to the shaft end of the rotating shaft, and the turbine blade disk has a plurality of turbine blades evenly distributed along the circumference, and the plurality of turbine blades are located at the output end of the combustor.

[0012] Compared with the prior art, the utility model has the following advantages: the utility model provides a swirl generator, and a plurality of igniters and a plurality of injectors are installed on one side of the burner inner cavity of the inner cylinder of the swirl generator; the full flow of liquid oxygen passes through the swirl generator, and its motion trajectory changes, so that the liquid oxygen moves centrifugally along the circumference in the burner, and the rotating liquid oxygen fluid has a relatively small impact on the inner cylinder at the center position, so that the igniter can ignite normally; a small amount of fuel is burned to gasify the low-temperature liquid oxygen to form combustion-supporting oxygen.

[0013] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0015] Figure 1 It is a structural cross-sectional view of the utility model.

[0016] Figure 2 It is a cross-sectional view of the turbine structure.

[0017] Figure 3 This is a side view of the burner of the swirl generator.

[0018] In the figure: 1. rotating shaft; 2. oxygen pump; 21. oxygen pump housing; 22. oxygen pump inducer; 23. oxygen pump centrifugal wheel; 24. oxygen pump bearing assembly; 3. turbine; 31. turbine housing; 32. burner; 33. turbine blade disk; 331. turbine blade; 34. turbine main bearing assembly; 4. swirl generator; 41. partition; 411. jet hole; 42. outer cylinder; 43. inner cylinder; 44. swirl blade; 5. igniter; 6. injector; 7. fuel manifold. DETAILED DESCRIPTION

[0019] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0021] In addition, in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it 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 a direct connection, or it can be indirectly connected through an intermediate medium, it can also be the internal communication of two components, it can be a wireless connection, or it can be a wired connection. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0022] In addition, the technical features involved in the different embodiments of the present invention described later can be combined with each other as long as they do not conflict with each other.

[0023] See also Figures 1 to 3 In an embodiment of the utility model, an oxygen-enriched turbopump for a full-flow staged combustion liquid rocket engine is characterized in that it includes an oxygen pump 2 and a turbine 3 coaxially sleeved on a rotating shaft 1, and a turbine 3 sealing device is provided on the side of the turbine 3 close to the oxygen pump 2; the setting of the turbine 3 sealing device prevents oxygen leakage and explosion, so the sealing device needs to withstand high temperature and high pressure, and at the same time adapt to the relative movement between the rotating shaft 1 and the turbine casing 31, and the sealing device adopts multi-stage sealing and special materials to provide a reliable sealing effect.

[0024] The turbine 3 includes a turbine casing 31, a burner 32, a turbine blade disk 33 and a turbine main bearing assembly 34. The outlet of the oxygen pump 2 is connected to the inside of the burner 32 through a swirl generator 4 installed at the input end of the burner 32. The swirl generator 4 includes a partition 41, an outer cylinder 42, an inner cylinder 43 and a group of swirl blades 44. A plurality of swirl blades 44 are arranged between the outer cylinder 42 and the inner cylinder 43 and are distributed at intervals along the circumferential direction. The partition 41 is provided with a plurality of jet holes 411 corresponding to the swirl blades 44. After the liquid oxygen passes through the jet holes 411, under the action of the swirl blades 44, its motion trajectory changes, so that the liquid oxygen moves centrifugally around the burner 32, and the rotating liquid oxygen fluid has relatively little effect on the inner cylinder 43 at the center.

[0025] Therefore, multiple igniters 5 and multiple injectors 6 are installed on one side of the inner cavity of the burner 32 of the inner cylinder 43. The injectors 6 are connected to the fuel manifold 7. The fuel manifold 7 inputs a small amount of liquid fuel to the injectors 6. The igniters 5 and injectors 6 installed on the inner cylinder 43 are not affected by the rotating liquid oxygen fluid. The injectors 6 atomize and spray the fuel, and the igniter 5 ignites the fuel. The combustion increases the temperature of the liquid oxygen and vaporizes it to form combustion-supporting oxygen.

[0026] In the next embodiment, the turbine blade disk 33 is fixedly connected to the axial end of the rotating shaft 1. The turbine blade disk 33 has multiple turbine blades 331 evenly distributed along the circumference. The multiple turbine blades 331 are located at the output end of the burner 32. The expansion force of the vaporized combustion-supporting oxygen drives the turbine 3 to rotate, and is discharged from the output end of the burner 32 and finally input into the main combustion chamber of the engine.

[0027] In the next embodiment, the oxygen pump 2 includes an oxygen pump housing 21, an oxygen pump inducer 22, an oxygen pump centrifugal wheel 23 and an oxygen pump bearing assembly 24; the oxygen pump housing 21 is provided with an oxygen pump 2 inlet and an oxygen pump 2 outlet, and the oxygen pump inducer 22 and the oxygen pump centrifugal wheel 23 are sleeved on the rotating shaft 1 between the oxygen pump 2 inlet and the oxygen pump 2 outlet through a spline connection; the rotating turbine 3 transmits torque to the pump wheel through the rotating shaft 1, so that the oxygen-rich turbine pump obtains a larger pump pressure to input a full flow of liquid oxygen.

[0028] In the next embodiment, the output end of the oxygen pump 2 is also connected to a liquid oxygen manifold connected to the inside of the rich burner. A small amount of liquid oxygen is input into the rich burner through the liquid oxygen manifold to burn a small amount of fuel kerosene and gasify the full flow kerosene to form combustible gas. Finally, the combustible gas is input into the main combustion chamber of the engine and mixed with the combustion-supporting oxygen to form thrust.

[0029] The turbine main bearing assembly 34 is installed between the rotating shaft 1 and the turbine housing 31, and the inner ring of the turbine main bearing assembly 34 is rotatably connected to the rotating shaft 1. The oxygen pump bearing assembly 24 is sleeved between the rotating shaft 1 and the oxygen pump housing 21. The turbine main bearing assembly 34 and the oxygen pump bearing assembly 24 rotatably connect the rotating shaft 1.

[0030] The above-mentioned oxygen-enriched turbine pump can be replaced with a methane turbine pump, and the solution of the utility model is still applicable. It is only necessary to design the size and casing of the methane turbine pump, or adjust some structures according to conventional needs.

[0031] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

Claims

1. An oxygen-enriched turbopump for a full-flow staged combustion liquid rocket engine, characterized in that: It comprises an oxygen pump and a turbine coaxially sleeved on a rotating shaft, wherein a turbine sealing device is arranged on a side of the turbine close to the oxygen pump; The oxygen pump comprises an oxygen pump housing, an oxygen pump inducer, an oxygen pump centrifugal wheel and an oxygen pump bearing assembly; the oxygen pump housing is provided with an oxygen pump inlet and an oxygen pump outlet, the oxygen pump inducer and the oxygen pump centrifugal wheel are sleeved on a rotating shaft between the oxygen pump inlet and the oxygen pump outlet through a spline connection, and the oxygen pump bearing assembly is sleeved between the rotating shaft and the oxygen pump housing; The turbine comprises a turbine housing, a burner, a turbine blade disk and a turbine main bearing assembly, the oxygen pump outlet is connected to the inside of the burner through a swirl generator installed at the burner input end, the swirl generator comprises a baffle, an outer cylinder, an inner cylinder and a group of swirl blades, a plurality of the swirl blades are arranged between the outer cylinder and the inner cylinder and are distributed at intervals along the circumferential direction, and the baffle is provided with a plurality of jet holes corresponding to the swirl blades; After the full flow of liquid oxygen passes through the jet hole, it is affected by the swirl blades and changes its trajectory, moving centrifugally in the burner to form a rotating fluid; A plurality of electric igniters and a plurality of injectors are installed on one side of the burner inner cavity of the inner cylinder. The injectors are connected to a fuel manifold, and the fuel manifold inputs a small amount of liquid fuel to the injectors.

2. The oxygen-enriched turbopump for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that: The oxygen pump output end is also connected to a liquid oxygen manifold communicating with the interior of the fuel-rich burner.

3. The oxygen-enriched turbopump for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that: The turbine main bearing assembly is installed between the rotating shaft and the turbine housing, and the inner ring of the turbine main bearing assembly is rotatably connected to the rotating shaft.

4. The oxygen-enriched turbopump for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that: The turbine blade disk is fixedly connected to the shaft end of the rotating shaft, and a plurality of turbine blades are evenly distributed on the turbine blade disk along the circumferential direction. The plurality of turbine blades are located at the output end of the burner.

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