Turbine pump for full-flow staged combustion liquid rocket engine

Abstract

The utility model discloses a turbine pump for a full-flow staged combustion liquid rocket engine. The turbine pump comprises a turbine shell, a pre-combustion chamber, a pump body, a turbine disc, a pump impeller and a rotor. A rotating pipeline is arranged in the pre-combustion chamber, the output pipe penetrates through the pre-combustion chamber to be connected with the bottom end of the rotating pipeline, and an outlet in the upper end of the rotating pipeline is formed in the outer ring wall of the pre-combustion chamber. The rotating pipeline extends the liquid oxygen conveying pipeline, so that heat in the pre-combustion chamber can fully heat liquid oxygen, it is guaranteed that the liquid oxygen is fully gasified, in the non-ideal state, part of ungasified liquid oxygen in the rotating pipeline is sprayed out from an outlet in the upper end of the rotating pipeline after being heated, and the liquid oxygen rotates on the outer ring wall of the pre-combustion chamber along the circumference; the igniter is not influenced; the problem that ignition is difficult in the prior art is solved, and the efficiency of the turbine pump is improved due to the design of the contraction exhaust port.

Description

Technical Field

[0001] The utility model specifically relates to a turbo pump for a full-flow staged combustion liquid rocket engine. Background Art

[0002] The turbo pump is a dynamic pump, the core part of the rocket engine. The turbo pump is a linkage device that uses the turbine to drive the pump to pressurize the liquid propulsion engine components - oxidizer and fuel. The high-temperature and high-pressure gas from the gas generator is used as the working fluid to drive the turbine to rotate, thereby driving the rotation of the pump. The oxidizer and fuel from the tank are pressurized by the pump and supplied to the thrust chamber.

[0003] Referring to the existing patent, a full-flow staged combustion liquid rocket turbo pump (CN217270523U), the patent installs both the combustion chamber and the igniter inside the pump body, and a turbine frame is installed at the bottom of the shell. A turbine is provided at the bottom of the turbine frame. The cryogenic fluid and the fuel are added to the pump body separately, and the fuel is ignited in the combustion chamber by the igniter. After combustion, the turbine below is driven to rotate and discharged from the outlet of the lower cover of the pump body. The rotating turbine can increase the pump pressure, thereby making the turbo pump pump pressure greater. Only a small part of the cryogenic fluid participates in the combustion, and the other flow fluid cools the combustion chamber and the turbine when passing through the combustion chamber and the turbine. The turbine and the combustion chamber are easier to cool, and the engine thrust is easier to adjust. However, the pre-combustion chamber of the prior art usually uses an electric igniter for ignition, and the temperature of liquid oxygen is below -183 degrees. When the full flow of liquid oxidant enters the pre-combustion chamber, it is easy to cool the electric igniter and cause ignition difficulties, thereby affecting the normal operation of the rocket engine. 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] A turbo pump for a full-flow staged combustion liquid rocket engine, comprising a turbine casing, a precombustion chamber, a pump body, a turbine disc, a pump impeller and a rotor; the precombustion chamber is annular, the outer side of the lower end of the inner ring wall thereof is sealedly connected to the pump body, and the lower end of the outer ring wall thereof is sealedly connected to the turbine casing; the turbine disc is mounted on one end of the rotor in the turbine casing, the pump impeller is mounted on the other end of the rotor in the pump body, and an output pipe is provided at the pump body outlet; a rotating pipeline is provided in the precombustion chamber, the output pipe passes through the precombustion chamber and is connected to the bottom end of the rotating pipeline, and the upper end outlet of the rotating pipeline is mounted on the outer ring wall in the precombustion chamber; a plurality of turbine blades are evenly arranged along the circumference of the turbine disc, an annular contraction exhaust port is provided at the annular output end of the precombustion chamber, and the turbine blades are arranged below the contraction exhaust port;

[0006] Preferably, the output end of the turbine housing is connected to the main combustion chamber of the engine through a conduit, and the output end of the turbine housing is also provided with a branch pipe, and the branch pipe is connected to the combustion chamber of another rich-fuel turbine pump;

[0007] Preferably, a plurality of bearings are installed between the pump body and the rotor, the inner ring of the bearing is rotatably connected to the rotor, and a plurality of sealing rings are also installed between the pump body and the rotor;

[0008] Preferably, the outer side of the outer annular wall of the pre-combustion chamber is also connected to a manifold, and the inner end of the manifold passes through the outer annular wall and is connected to the inner cavity of the pre-combustion chamber.

[0009] Compared with the prior art, the advantages of the utility model are: the rotating pipeline of the utility model extends the liquid oxygen delivery pipeline, so that the heat in the pre-combustion chamber can fully heat the liquid oxygen, ensuring that the liquid oxygen is fully vaporized. Under undesirable conditions, part of the unvaporized liquid oxygen in the rotating pipeline is heated and ejected from the upper end outlet of the rotating pipeline and rotates around the outer ring wall of the pre-combustion chamber, without affecting the igniter. The utility model solves the problem of ignition difficulty in the prior art, and the design of the contracted exhaust port improves the efficiency of the turbopump.

[0010] 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

[0011] 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.

[0012] Figure 1 It is a structural schematic diagram of the utility model.

[0013] In the figure: 1. turbine housing; 11. branch pipe; 2. pre-combustion chamber; 21. rotating pipeline; 22. contraction exhaust port; 3. pump body; 31. output pipe; 4. turbine disk; 41. turbine blades; 5. pump impeller; 6. rotor; 7. manifold; 8. bearing; 9. sealing ring; 10. turbine housing output end. DETAILED DESCRIPTION

[0014] 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.

[0015] 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.

[0016] 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.

[0017] In addition, the technical features involved in the different embodiments of the utility model described later can be combined with each other as long as they do not conflict with each other.

[0018] See also Figure 1 In this embodiment, a turbopump for a full-flow staged combustion liquid rocket engine comprises a turbine casing 1, a precombustion chamber 2, a pump body 3, a turbine disc 4, a pump impeller 5 and a rotor 6; the precombustion chamber 2 is annular, the outer side of the lower end of its inner ring wall is sealed and connected to the pump body 3, and the lower end of its outer ring wall is sealed and connected to the turbine casing 1; the turbine disc 4 is mounted on one end of the rotor 6 in the turbine casing 1, the pump impeller 5 is mounted on the other end of the rotor 6 in the pump body 3, and an output pipe 31 is provided at the outlet of the pump body 3; a rotating pipeline 21 is provided in the precombustion chamber 2, the output pipe 31 passes through the precombustion chamber 2 and is connected to the bottom end of the rotating pipeline 21, and the upper end outlet of the rotating pipeline 21 is mounted on the outer ring wall in the precombustion chamber 2.

[0019] In this embodiment, an oxygen-rich turbine pump is taken as an example. Under the action of the pump impeller 5, the full flow of liquid oxygen is introduced from the output pipe 31 of the pump body 3 into the rotating pipeline 21. The rotating pipeline 21 extends the liquid oxygen delivery pipeline, so that the heat in the precombustion chamber 2 can fully heat the liquid oxygen, ensuring that the liquid oxygen is fully vaporized, and the vaporized oxygen is sprayed into the precombustion chamber 2 at full flow; a small amount of fuel gas directly enters the precombustion chamber 2 through the manifold 7 from the output end of another fuel-rich turbine pump, and the fuel gas is ignited by the igniter. Since the oxidant and the fuel are both in a gaseous state, it is easier to enter the combustion state and will not affect the igniter.

[0020] In this embodiment, the upper end outlet of the rotating pipeline 21 is installed on the outer ring wall in the pre-combustion chamber 2. Under undesirable conditions, part of the ungasified liquid oxygen in the rotating pipeline 21 is heated and mixed with oxygen, and then sprayed from the upper end outlet of the rotating pipeline 21 to the pre-combustion chamber 2. The outer ring wall of the pre-combustion chamber 2 makes the oxidant mixture rotate around and gasify in the combustion environment, which has no effect on the igniter. The utility model solves the problem of ignition difficulty in the prior art.

[0021] In the next embodiment, a plurality of turbine blades 41 are evenly arranged along the circumference of the turbine disk 4, and a ring-shaped contraction exhaust port 22 is arranged at the annular output end of the pre-combustion chamber 2. When the oxygen-rich gas expanded in the pre-combustion chamber 2 passes through the contraction exhaust port 22, the oxygen-rich gas is accelerated, and the turbine blades 41 arranged below the contraction exhaust port 22 are driven by the accelerated gas to run quickly, thereby transmitting the torque to the pump impeller 5 through the rotor 6, so that the turbo pump increases the pump pressure. The design of the contraction exhaust port 22 improves the efficiency of the turbo pump.

[0022] In this embodiment, the turbine housing output end 10 is connected to the main combustion chamber of the engine through a conduit, and the combustion-supporting oxygen-rich gas is input into the main combustion chamber to be mixed with the combustible fuel-rich gas for combustion, so that the engine generates thrust. The turbine housing output end 10 is also provided with a branch pipe 11, so that a small amount of oxygen-rich gas is input into the combustion chamber of another fuel-rich turbine pump through the branch pipe 11 and participates in the combustion support.

[0023] A plurality of bearings 8 are installed between the pump body 3 and the rotor 6 , and the inner rings of the bearings 8 are rotatably connected to the rotor 6 . A plurality of sealing rings 9 are also installed between the pump body 3 and the rotor 6 .

[0024] In another embodiment, the utility model can also be a fuel-rich turbopump, which only requires modification of dimensions and data.

[0025] 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. A turbopump for a full-flow staged combustion liquid rocket engine, characterized in that: It includes turbine housing, pre-combustion chamber, pump body, turbine disc, pump impeller and rotor; The pre-combustion chamber is in the shape of a ring, the outer side of the lower end of the inner ring wall is sealed to the pump body, and the lower end of the outer ring wall is sealed to the turbine housing; The turbine disc is mounted on one end of the rotor in the turbine housing, the pump impeller is mounted on the other end of the rotor in the pump body, and the pump body outlet is provided with an output pipe; A rotating pipeline is arranged in the pre-combustion chamber, the output pipe passes through the pre-combustion chamber and is connected to the bottom end of the rotating pipeline, and the upper end outlet of the rotating pipeline is installed on the outer ring wall in the pre-combustion chamber; The turbine disc is evenly provided with a plurality of turbine blades along the circumference, the annular output end of the pre-combustion chamber is provided with an annular contraction exhaust port, and the turbine blades are arranged below the contraction exhaust port.

2. The turbo pump for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that: The output end of the turbine housing is connected to the main combustion chamber of the engine through a conduit. The output end of the turbine housing is also provided with a branch pipe, which is connected to the combustion chamber of another rich-fuel turbine pump.

3. The turbo pump for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that: A plurality of bearings are installed between the pump body and the rotor, the inner rings of the bearings are rotatably connected to the rotor, and a plurality of sealing rings are also installed between the pump body and the rotor.

4. The turbo pump for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that: The outer side of the outer annular wall of the pre-combustion chamber is also connected to a manifold, and the inner end of the manifold passes through the outer annular wall and communicates with the inner cavity of the pre-combustion chamber.

Images