Full-flow afterburning circulating thrust chamber and cooling method thereof

Abstract

The invention discloses a full-flow afterburning circulation thrust chamber and a cooling method thereof. The problem that in the prior art, the working efficiency of an engine is reduced is solved. A path of high-temperature fuel-rich or oxygen-rich fuel gas is led out from the exhaust end of the gas turbine and is input into the thrust chamber body through the fuel gas branch pipe and the fuel gas cooling collector to serve as a membrane coolant of the thrust chamber body, and an engine does not need to independently lead a path of high-pressure low-temperature fuel behind a fuel pump to serve as the membrane coolant of the thrust chamber body; the specific impulse performance of the engine can be improved by nearly 1%, and the pressure loss can be reduced by more than one time.

Description

Technical Field

[0001] The present invention relates to a thrust chamber and its cooling method, and particularly to a full-flow staged combustion cycle thrust chamber and its cooling method. Background Art

[0002] A full-flow staged combustion cycle liquid rocket engine includes two gas generators: an oxygen-rich gas generator and a fuel-rich gas generator. Liquid oxygen and methane are converted into high-temperature fuel-rich gas and high-temperature oxygen-rich gas through the two gas generators. Since the full-flow staged combustion system converts all the propellants into high-temperature gas to drive the turbine to do work, a high engine efficiency can be obtained. However, at the same time, it also leads to the problem that the thrust chamber faces severe insufficient thermal protection.

[0003] For a traditional staged combustion cycle engine, in order to ensure the reliable operation of the thrust chamber, a small part of the propellant is sprayed onto the combustion chamber wall of the thrust chamber to form a protective film to isolate the high-temperature gas and improve the reliability of the combustion chamber operation. This part of the propellant does not enter the gas generator to be converted into high-temperature gas and thus cannot enter the gas turbine to do work. Therefore, the efficiency of the engine will decrease. The greater the flow rate of the propellant used for film cooling, the greater the decrease in efficiency, generally decreasing by 1% - 3%. Summary of the Invention

[0004] In order to solve the technical problem in the prior art that in order to ensure the reliable operation of the thrust chamber, usually a small part of the propellant is sprayed onto the combustion chamber wall of the thrust chamber to form a protective film, and the propellant entering the thrust chamber does not enter the gas generator to be converted into high-temperature gas and thus cannot enter the gas turbine to do work, resulting in a reduction in the working efficiency of the engine, the present invention provides a full-flow staged combustion cycle thrust chamber and its cooling method.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A full-flow staged combustion cycle thrust chamber, characterized in that:

[0007] It includes a gas generator for generating high-temperature and high-pressure gas, a gas turbine with its input end connected to the output end of the gas generator, a thrust chamber body, a gas main pipeline with one end connected to the exhaust end of the gas turbine, a gas branch pipeline with one end communicating with the middle part of the gas main pipeline, a gas collector wound circumferentially on the outer wall of the thrust chamber body and communicating with the other end of the gas main pipeline, and N gas cooling collectors wound circumferentially on the outer wall of the thrust chamber body and communicating with the other end of the gas branch pipeline; where N is 1, 2 or 3;

[0008] A injector panel is provided in the thrust chamber body along its radial cross-section, dividing the thrust chamber body into a pre-gas injection chamber above the injector panel and a combustion chamber below the injector panel. A plurality of nozzles penetrating up and down are provided on the injector panel.

[0009] The inner cavity of the gas collector is communicated with the pre-gas injection chamber through a plurality of first ventilation holes arranged on the side wall of the thrust chamber body;

[0010] The inner cavity of the gas cooling collector is communicated with the combustion chamber through a plurality of second ventilation holes arranged on the side wall of the thrust chamber body.

[0011] Further, the included angle between the axis of the second ventilation hole and the inner wall of the thrust chamber body is 10° to 20°.

[0012] Further, the orifice of the second ventilation hole is tangent to the inner wall of the thrust chamber body.

[0013] Further, both the gas collector and the gas cooling collector are C-shaped gas collectors, and their C-shaped open ends are fixedly connected to the outer wall of the thrust chamber body respectively.

[0014] Further, a throttle orifice plate is arranged in the gas branch pipe.

[0015] Further, the gas cooling collector includes N = 2, namely a gas cooling I-way collector and a gas cooling II-way collector;

[0016] The gas cooling I-way collector is communicated with the gas branch pipe through a cooling I pipeline;

[0017] The gas cooling II-way collector is communicated with the gas branch pipe through a cooling II pipeline.

[0018] Further, two throttle orifice plates are arranged in the gas branch pipe;

[0019] One throttle orifice plate is arranged in the gas branch pipe between the cooling I pipeline and the cooling II pipeline, and the other throttle orifice plate is arranged in the gas branch pipe on the side of the cooling I pipeline away from the cooling II pipeline.

[0020] A cooling method for a full-flow staged combustion cycle thrust chamber, which is used for the above-mentioned full-flow staged combustion cycle thrust chamber, is characterized in that it includes the following steps:

[0021] Step 1, the gas generator burns the propellant to generate high-temperature and high-pressure gas and outputs it to the gas turbine;

[0022] Step 2, the high-temperature and high-pressure gas drives the gas turbine to do work for external equipment use, and the gas after doing work is divided into 1 + N paths through the gas main pipeline and the gas branch pipe and enters the gas collector and N gas cooling collectors respectively;

[0023] Step 3: The fuel gas entering the fuel gas collector enters the pre-injection chamber of the fuel gas through the first vent hole, and then is injected into the combustion chamber through the nozzles on the injector panel and burns in the inner cavity of the combustion chamber; the fuel gas entering the fuel gas cooling collector enters the combustion chamber through the second vent hole to cool the inner wall of the combustion chamber.

[0024] Further, in step 1, the propellant is liquid oxygen and fuel; the fuel is liquid methane, kerosene or liquid hydrogen.

[0025] Further, in step 2, the fuel gas entering the fuel gas collector is more than 80% of the fuel gas discharged from the gas turbine.

[0026] Advantages of the present invention:

[0027] 1. A full-flow staged combustion cycle thrust chamber and its cooling method provided by the present invention lead a path of high-temperature fuel-rich or oxygen-rich fuel gas from the exhaust end of the gas turbine, and input it into the thrust chamber body through the fuel gas branch pipe and the fuel gas cooling collector as the film coolant of the thrust chamber body. The engine does not need to lead a path of high-pressure low-temperature fuel from behind the fuel pump as the film coolant of the thrust chamber body. The specific impulse performance of the engine can be increased by nearly 1%, and the pressure loss can be reduced by more than 1 time.

[0028] 2. In the present invention, the exhaust end of the gas turbine is connected to the thrust chamber body by a pipeline, and the connection method is welding or flange plus bolt fastening. 1-3 cooling pipelines can be set according to needs, and valves for controlling the on / off of the cooling pipelines do not need to be set in the middle of the pipelines. The system structure is simple and the cost is low.

[0029] 3. In the present invention, the orifice of the second through hole is tangent to the inner wall of the thrust chamber, which is more conducive to forming a film coolant on the inner wall of the thrust chamber body and improving the cooling efficiency.

[0030] 4. A throttle orifice plate is arranged in the fuel gas branch pipe of the present invention to facilitate the control of the fuel gas volume flowing into the fuel gas cooling collector.

[0031] 5. Two fuel gas cooling collectors are arranged on the thrust chamber body of the present invention, which can take both cooling efficiency and cooling cost into consideration. Description of the Drawings

[0032] Figure 1 is a schematic structural diagram of an embodiment of a full-flow staged combustion cycle thrust chamber of the present invention;

[0033] Figure 2 is the present invention Figure 1 The partial enlarged view at A;

[0034] Figure 3 is the present invention Figure 1 The partial enlarged view at B;

[0035] Reference Numerals in the Drawings:

[0036] 1 - Gas generator, 2 - Gas turbine, 3 - Thrust chamber body, 31 - Injector panel, 32 - Premixing chamber for gas injection, 33 - Combustion chamber, 34 - Nozzle, 35 - First vent hole, 36 - Second vent hole, 4 - Orifice plate, 6 - Gas collector, 7 - Gas cooling path I collector, 8 - Gas cooling path II collector, 9 - Main gas pipeline, 10 - Gas branch pipeline, 11 - Cooling path I pipeline, 12 - Cooling path II pipeline. Detailed Embodiment

[0037] The technical solution of the present invention will be clearly and completely described below in conjunction with the drawings and embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0038] A full - flow staged combustion cycle thrust chamber provided in this embodiment, as Figure 1 shown, includes a gas generator 1 for generating high - temperature and high - pressure gas, a gas turbine 2 whose input end is connected to the output end of the gas generator 1, a thrust chamber body 3, a main gas pipeline 9 whose one end is connected to the exhaust end of the gas turbine 2, a gas branch pipeline 10 whose one end is connected to the middle of the main gas pipeline 9, a gas collector 6 wound circumferentially on the outer wall of the thrust chamber body 3 and connected to the other end of the main gas pipeline 9, and N gas cooling collectors wound circumferentially on the outer wall of the thrust chamber body and connected to the other end of the gas branch pipeline 10; where N is 1, 2 or 3; in this embodiment, the gas cooling collectors include N = 2, namely a gas cooling path I collector 7 and a gas cooling path II collector 8; the gas cooling path I collector 7 is connected to the gas branch pipeline 10 through a cooling path I pipeline 11; the gas cooling path II collector 8 is connected to the gas branch pipeline 10 through a cooling path II pipeline 12.

[0039] An injector panel 31 is provided in the thrust chamber body 3 along its radial cross - section, dividing the thrust chamber body 3 into a premixing chamber for gas injection 32 above the injector panel 31 and a combustion chamber 33 below the injector panel 31, and a plurality of nozzles 34 penetrating up and down are provided on the injector panel 31.

[0040] Both the gas collector 6 and the gas cooling collectors are C - shaped gas collectors, and their C - shaped open ends are respectively fixedly connected to the outer wall of the thrust chamber body 3 to form a gas collection inner cavity. As Figure 2 shown, the inner cavity of the gas collector 6 is connected to the premixing chamber for gas injection 32 through a plurality of first vent holes 35 provided on the side wall of the thrust chamber body 3; as Figure 3As shown, the inner cavities of the gas cooling I-way collector 7 and the gas cooling II-way collector 8 are respectively communicated with the combustion chamber 33 through a plurality of second ventilation holes 36 provided on the side wall of the thrust chamber body 3; the included angle between the axis of the second ventilation hole 36 and the inner wall of the thrust chamber body 3 is 10° to 20° or its orifice is tangent to the inner wall of the thrust chamber body 3.

[0041] Two throttle orifice plates 4 are provided in the gas branch pipe 10; one throttle orifice plate 4 is provided in the gas branch pipe 10 between the cooling I pipeline 11 and the cooling II pipeline 12, and the other throttle orifice plate 4 is provided in the gas branch pipe 10 on the side of the cooling I pipeline 11 away from the cooling II pipeline 12.

[0042] The gas main pipeline 9 is communicated with the gas collector 6 through a connection method of welding or flange plus bolt fastening. Similarly, the cooling I pipeline 11 and the cooling II pipeline 12 are respectively communicated with the gas cooling I-way collector 7 and the gas cooling II-way collector 8 through a connection method of welding or flange plus bolt fastening.

[0043] The cooling method of the above full-flow staged combustion cycle thrust chamber includes the following steps:

[0044] Step 1, the gas generator 1 burns the propellant to generate high-temperature and high-pressure gas and outputs it to the gas turbine 2; the propellant is a mixture of an oxidizer and a fuel.

[0045] The function of the gas generator 1 is to generate high-temperature and high-pressure gas. It uses liquid oxygen and fuel as the propellant. The fuel is not limited to liquid methane, kerosene or liquid hydrogen. The gas can be rich-burn gas or oxygen-rich gas. Taking liquid oxygen and methane as an example, when the generated gas is rich-burn gas, the mixing ratio of the gas generator 1 is generally less than 1, and when the generated gas is oxygen-rich gas, the mixing ratio of the gas generator 1 is generally greater than 50.

[0046] Step 2, the gas blows the gas turbine 2 to do work. The gas is the driving medium for the gas turbine 2 to do work. The gas blows the gas turbine 2, and the gas turbine 2 drives the pump, and the pump pressurizes other media.

[0047] The gas after doing work is divided into 1 + N paths through the gas main pipeline 9 and the gas branch pipe 10 and enters the gas collector 6 and N gas cooling collectors respectively; in this embodiment, the gas entering the gas collector 6 is more than 80% of the gas discharged from the gas turbine 2.

[0048] Step 3, the gas entering the gas collector 6 enters the pre-gas injection chamber 32 through the first ventilation hole 35, and then is sprayed into the combustion chamber 33 through the nozzles 34 on the injector panel 31 and burns in the inner cavity of the combustion chamber 33; the gas entering the gas cooling collector enters the combustion chamber 33 through the second ventilation hole 36 to form an attached gas film to reliably cool the inner wall of the combustion chamber 33.

[0049] With the full-flow staged combustion cycle thrust chamber of this embodiment, the engine does not need to separately draw a high-pressure cryogenic fuel from the rear of the fuel pump as the film coolant for the thrust chamber. The specific impulse performance of the engine can be increased by nearly 1%, and the pressure loss can be reduced by more than 1 time.

[0050] As described above, the above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A full-flow staged combustion cycle thrust chamber, characterized in that: It includes a gas generator (1) for generating high-temperature and high-pressure gas, a gas turbine (2) with its input end connected to the output end of the gas generator (1), a thrust chamber body (3), a gas main pipeline (9) with one end connected to the exhaust end of the gas turbine (2), a gas branch pipe (10) with one end communicating with the middle of the gas main pipeline (9), a gas collector (6) wound circumferentially on the outer wall of the thrust chamber body and communicating with the other end of the gas main pipeline (9), and N gas cooling collectors wound circumferentially on the outer wall of the thrust chamber body and communicating with the other end of the gas branch pipe (10); where N is 1, 2 or 3; Inside the thrust chamber body (3), an injector panel (31) is provided along its radial section, dividing the thrust chamber body (3) into a pre-gas injection chamber (32) above the injector panel (31) and a combustion chamber (33) below the injector panel (31), and a plurality of nozzles (34) penetrating up and down are provided on the injector panel (31); The inner cavity of the gas collector (6) communicates with the pre-gas injection chamber (32) through a plurality of first vent holes (35) provided on the side wall of the thrust chamber body (3); The inner cavity of the gas cooling collector communicates with the combustion chamber (33) through a plurality of second vent holes (36) provided on the side wall of the thrust chamber body (3).

2. The full-flow staged combustion cycle thrust chamber according to claim 1, characterized in that: The included angle between the axis of the second vent hole (36) and the inner wall of the thrust chamber body (3) is 10° to 20°.

3. The full-flow staged combustion cycle thrust chamber according to claim 1, characterized in that: The orifice of the second vent hole (36) is tangent to the inner wall of the thrust chamber body (3).

4. The full-flow staged combustion cycle thrust chamber according to claim 2 or 3, characterized in that: Both the gas collector (6) and the gas cooling collector are C-shaped gas collectors, and their C-shaped open ends are fixedly connected to the outer wall of the thrust chamber body (3) respectively.

5. The full-flow staged combustion cycle thrust chamber according to claim 4, characterized in that: A throttle orifice plate (4) is provided in the gas branch pipe (10).

6. The full-flow staged combustion cycle thrust chamber according to claim 5, characterized in that: There are N = 2 gas cooling collectors, namely a gas cooling I-way collector (7) and a gas cooling II-way collector (8); The gas cooling I-way collector (7) communicates with the gas branch pipe (10) through a cooling I pipeline (11); The gas cooling II-way collector (8) communicates with the gas branch pipe (10) through a cooling II pipeline (12).

7. The full-flow staged combustion cycle thrust chamber according to claim 6, characterized in that: Two throttle orifice plates (4) are provided in the gas branch pipe (10); One throttle orifice plate (4) is provided in the gas branch pipe (10) between the cooling I pipeline (11) and the cooling II pipeline (12), and the other throttle orifice plate (4) is provided in the gas branch pipe (10) on the side of the cooling I pipeline (11) away from the cooling II pipeline (12).

8. A cooling method for a full-flow staged combustion cycle thrust chamber, which is used for the full-flow staged combustion cycle thrust chamber according to any one of claims 1-7, characterized in that, It includes the following steps: Step 1: The gas generator (1) burns the propellant to generate high-temperature and high-pressure gas and outputs it to the gas turbine (2). Step 2: The high-temperature and high-pressure gas drives the gas turbine (2) to do work for external equipment use. The gas after doing work is divided into 1+N paths through the gas main pipeline (9) and the gas branch pipes (10) and enters the gas collector (6) and N gas cooling collectors respectively. Step 3: The gas entering the gas collector (6) enters the pre-injection gas chamber (32) through the first ventilation hole (35), and then is injected into the combustion chamber (33) through the nozzles (34) on the injector panel (31) and burns in the inner cavity of the combustion chamber (33). The gas entering the gas cooling collector enters the combustion chamber (33) through the second ventilation hole (36) to cool the inner wall of the combustion chamber (33).

9. The cooling method of the full-flow staged combustion cycle thrust chamber according to claim 8, characterized in that: In step 1, the propellant is liquid oxygen and fuel; the fuel is liquid methane, kerosene or liquid hydrogen.

10. The cooling method of the full-flow staged combustion cycle thrust chamber according to claim 9, characterized in that: In step 2, the gas entering the gas collector (6) is more than 80% of the gas discharged from the gas turbine (2).

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