CN112628019A - Afterburning cycle engine thrust chamber injector cooling flow path and design method thereof - Google Patents
Afterburning cycle engine thrust chamber injector cooling flow path and design method thereof Download PDFInfo
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- CN112628019A CN112628019A CN202011509936.9A CN202011509936A CN112628019A CN 112628019 A CN112628019 A CN 112628019A CN 202011509936 A CN202011509936 A CN 202011509936A CN 112628019 A CN112628019 A CN 112628019A
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- thrust chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Abstract
The invention relates to a cooling flow path of an injector of a thrust chamber of a afterburning cycle engine and a design method thereof. The invention aims to solve the technical problems that when an existing afterburning cycle engine cools a thrust chamber injector panel, high-pressure liquid is directly introduced from the back of a main pump to cool the injector panel, a large throttle ring is required to be arranged on a flow path for throttling, power loss is caused by the throttle ring, the load of the main pump is increased, the temperature of a gas generator is increased, and the operation of a main turbine is not facilitated. According to the invention, the fuel or oxidant introduced from the back of the main pump drives the pre-pressing turbine pump and then cools the injector panel, the introduced fuel or oxidant firstly applies work to the pre-pressing turbine pump and then cools the injector panel, so that the power is saved, and the problems of load increase of the main pump and temperature rise of the gas generator caused by directly introducing high-pressure liquid from the back of the main pump to cool the injector panel are solved.
Description
Technical Field
The invention relates to an afterburning cycle engine, in particular to a cooling flow path of an injector of a thrust chamber of an afterburning cycle engine and a design method thereof.
Background
For a part of pumping type afterburning cycle engines, in order to ensure reliable operation of a thrust chamber, a thrust chamber injector panel needs to be cooled, a common method is to directly introduce high-pressure liquid from a main pump (a fuel main pump or an oxidant main pump) to cool the injector panel, and a large throttle ring throttle needs to be arranged on a flow path, and the defects are that the throttle ring causes power loss, so that the load of the main pump is increased, the temperature of a gas generator is increased, and the operation of a main turbine is not facilitated.
In addition, in order to ensure that the main pumps (the fuel main pump and the oxidant main pump) can work reliably at high rotating speed, the inlet pressure requirement of the main pumps is high, and due to the weight reduction of the arrow body, the wall thickness of the arrow body fuel storage tank and the wall thickness of the oxidant storage tank are thin, the pressure of the storage tanks is low, and a pre-pressing turbine pump (namely the fuel pre-pressing turbine pump and the oxidant pre-pressing turbine pump) needs to be arranged at the inlet of the main pumps to improve the inlet pressure of the main pumps. Taking the fuel pre-pressurizing turbine pump as an example, since the post-combustion engine often adopts a way of high-pressure fuel branched from the outlet of the main fuel pump to drive the fuel pre-pressurizing turbine, the driving method can also increase the load of the main fuel pump and the temperature of the gas generator, which is not beneficial to the operation of the main fuel turbine. And, shunt fuel from fuel main pump export and drive fuel pre-compaction turbopump, only when fuel main pump outlet pressure reaches a definite value, the reposition of redundant personnel fuel flow path just can play the drive effect to fuel pre-compaction turbine, when fuel main pump outlet pressure is lower, fuel pre-compaction turbopump does not play the spin, the pump of fuel pre-compaction turbopump is difficult to play and improves the lift effect, fuel main pump entrance is in low pressure state, when starting, because fuel main pump entry flow is great, inertial loss is great, cause the fuel main pump to take place the cavitation easily. The same problem exists with oxidizer pre-compression turbopumps.
Disclosure of Invention
The invention aims to solve the technical problems that when an existing afterburning cycle engine cools a thrust chamber injector panel, high-pressure liquid is directly introduced from the back of a main pump to cool the injector panel, a large throttle ring is required to be arranged on a flow path for throttling, and the throttle ring causes power loss, so that the load of the main pump is increased, the temperature of a gas generator is increased, and the working of a main turbine is not facilitated.
In order to solve the technical problems, the technical solution provided by the invention is as follows:
the invention also provides a cooling flow path of the injector of the thrust chamber of the afterburning cycle engine, which comprises a fuel main pump, an oxidant main pump, a fuel gas generator and the thrust chamber, wherein the wall of the thrust chamber is internally provided with a cooling flow path of the thrust chamber, and the cooling flow path is characterized in that:
the fuel pre-pressing turbine pump is coaxially arranged with the fuel main pump; the outlet of the main fuel pump is connected with the inlet of a thrust chamber cooling flow path, the outlet pipeline of the thrust chamber cooling flow path is divided into two paths, and one path of the outlet pipeline passes through the turbine end of the fuel pre-pressing turbine pump and then leads to the injector panel of the thrust chamber and is used for driving the fuel pre-pressing turbine pump and cooling the injector panel; the other path is used for being directly connected with the inlet of the gas generator; the outlet of the oxidant main pump is connected with the inlet of the fuel gas generator;
or the system also comprises an oxidant prepressing turbine pump which is coaxially arranged with the oxidant main pump; the outlet of the oxidant main pump is connected with the inlet of the thrust chamber cooling flow path, the outlet pipeline of the thrust chamber cooling flow path is divided into two paths, and one path of the outlet pipeline passes through the turbine end of the oxidant pre-pressing turbine pump and then leads to the injector panel of the thrust chamber and is used for driving the oxidant pre-pressing turbine pump and cooling the injector panel; the other path is used for being directly connected with the inlet of the gas generator; the outlet of the fuel main pump is connected with the inlet of the fuel gas generator.
Further, the gas generator is a rich burn generator and/or a rich oxygen generator, as the case may be.
The invention also provides a design method of the cooling flow path of the injector of the thrust chamber of the afterburning cycle engine, which aims at the cooling flow path of the injector of the thrust chamber of the afterburning cycle engine and is characterized by comprising the following steps:
the fuel is sent into a thrust chamber cooling flow path through an inlet of the thrust chamber cooling flow path through a fuel main pump, the fuel sent into the thrust chamber cooling flow path is gasified and exchanges heat at the initial stage of starting, generated gas flows out of an outlet of the thrust chamber cooling flow path and then is divided into two paths, one path of the generated gas is divided into two paths before a fuel generator is ignited, the turbine of a fuel pre-pressing turbine pump applies work, the gas after applying the work re-cools an injector panel of the thrust chamber, and the other path of the generated gas directly flows into the fuel generator;
or the oxidant is sent into the thrust chamber cooling flow path through the inlet of the thrust chamber cooling flow path by the oxidant main pump, the oxidant sent into the thrust chamber cooling flow path is gasified and exchanges heat at the initial stage of starting, generated gas flows out from the outlet of the thrust chamber cooling flow path and then is divided into two paths, one path of gas does work on the turbine of the oxidant pre-pressing turbine pump before the gas generator is ignited, the gas after the work does work cools the injector panel of the thrust chamber, and the other path of gas directly flows into the gas generator.
Compared with the prior art, the invention has the following beneficial effects:
1. compared with the existing high-pressure liquid cooling injector panel directly led from the back of a main pump, the high-pressure liquid cooling injector panel needs to be provided with a larger throttle ring for throttling on the flow path, and the throttle ring causes power loss.
2. The invention provides a thrust chamber injector cooling flow path of a afterburning cycle engine and a design method thereof.A precompressed turbopump driving flow path is led out from an outlet of a thrust chamber cooling flow path, and the starting time of a precompressed turbine is advanced, compared with the prior art that when high-pressure fuel or oxidant is shunted from the rear of a main pump to drive the precompressed turbopump, the drainage flow can only drive the precompressed turbopump when the outlet pressure of the main pump reaches a certain value, and the time is after a gas generator is ignited for a certain time, the invention adopts a drainage scheme from the outlet of the thrust chamber cooling flow path, when low-temperature fuel or oxidant flows through the thrust chamber cooling flow path, a large amount of gasification heat exchange is carried out in a slender flow passage of the thrust chamber cooling flow path at the initial stage of starting, the generated gas has certain working capacity, and before the gas generator is ignited, the moment when the pre-pressing turbine starts to drive is advanced, and the working condition of the main pump is optimized.
3. According to the afterburning cycle engine thrust chamber injector cooling flow path and the design method thereof, fuel or oxidant is led from the outlet of the thrust chamber cooling flow path to drive the pre-pressing turbine pump, and is heated by the thrust chamber, compared with the fuel or oxidant directly led from the outlet of the main pump, the fuel or oxidant has higher temperature and lower density, so that the fuel or oxidant at the outlet of the thrust chamber cooling flow path has stronger acting capacity than the fuel or oxidant at the inlet of the thrust chamber cooling flow path, the driving flow can be reduced, and the power of the main pump is saved.
Drawings
FIG. 1 is a schematic illustration of the afterburner engine thrust chamber injector cooling flow path of the present invention;
description of reference numerals:
the fuel-rich combustion system comprises a fuel main pump 1, an oxidizer main pump 2, a thrust chamber 3, a fuel pre-pressurizing turbine pump 4, a turbine end 41, an inlet of a thrust chamber cooling flow path 5, an outlet of a thrust chamber cooling flow path 6, a rich combustion generator 7 and a rich oxygen generator 8.
Detailed Description
The invention is further described below with reference to the figures and examples.
The cooling flow path of the injector of the thrust chamber of the afterburning cycle engine comprises a fuel main pump 1, an oxidant main pump 2, a gas generator and a thrust chamber 3, wherein a thrust chamber cooling flow path is arranged in the wall of the thrust chamber 3.
The afterburning cycle engine thrust chamber injector cooling flow path also comprises a fuel pre-pressurizing turbine pump 4 which is coaxial with the fuel main pump 1; the outlet of the fuel main pump 1 is connected with the inlet 5 of the thrust chamber cooling flow path, the outlet 6 pipeline of the thrust chamber cooling flow path is divided into two paths, one path of the pipeline passes through the turbine end 41 of the fuel pre-pressing turbine pump 4 and then leads to the injector panel of the thrust chamber 3, and the pipeline is used for driving the fuel pre-pressing turbine pump 4 and cooling the injector panel; the other path is used for being directly connected with the inlet of the gas generator; the outlet of the oxidant main pump 2 is connected with the inlet of the gas generator;
or, the system also comprises an oxidant precompression turbopump which is coaxial with the oxidant main pump 2; the outlet of the oxidant main pump 2 is connected with the inlet 5 of the thrust chamber cooling flow path, the outlet 6 pipeline of the thrust chamber cooling flow path is divided into two paths, one path of the pipeline passes through the turbine end of the oxidant pre-pressing turbine pump and then leads to the injector panel of the thrust chamber 3, and the pipeline is used for driving the oxidant pre-pressing turbine pump and cooling the injector panel; the other path is used for being directly connected with the inlet of the gas generator; the outlet of the fuel main pump 1 is connected with the inlet of the gas generator.
The gas generator is a rich gas generator 7 and/or a rich gas generator 8.
A method for designing a cooling flow path of an injector of a thrust chamber of an afterburning cycle engine comprises the following steps:
fuel is sent into a thrust chamber cooling flow path through a thrust chamber cooling flow path inlet 5 by a fuel main pump 1, the fuel sent into the thrust chamber cooling flow path is gasified and heat-exchanged at the initial stage of starting, generated gas flows out of a thrust chamber cooling flow path outlet 6 and then is divided into two paths, one path of the gas does work on a turbine of a fuel pre-pressing turbine pump 4 before a gas generator is ignited, the gas after the work does re-cool an injector panel of the thrust chamber 3, and the other path of the gas directly flows into the gas generator;
or, the oxidant is sent into the thrust chamber cooling flow path through the thrust chamber cooling flow path inlet 5 by the oxidant main pump 2, the oxidant sent into the thrust chamber cooling flow path is gasified and heat-exchanged at the initial stage of starting, the generated gas flows out from the thrust chamber cooling flow path outlet 6 and then is divided into two paths, one path performs work on the turbine of the oxidant pre-pressing turbine pump 4 before the gas generator is ignited, the gas after the work performs re-cooling the injector panel of the thrust chamber 3, and the other path directly flows into the gas generator.
Taking the fuel-driven fuel-pre-pressurizing turbo pump 4 as an example:
assuming that the fuel medium is directly led out from the outlet of the fuel main pump 1 and works on the fuel pre-pressure turbine, the flow rate of the fuel-driven fuel pre-pressure turbine pump needs to satisfy the equations (1) and (2), wherein P1Preloading turbine power, q, for fuelm1Preloading the turbine flow, p, for fueli1Preloading turbine inlet pressure, p, for fuele1Preloading a turbine outlet pressure, ρ, for fuel1The density of a fuel medium, eta is the efficiency of the fuel pre-pressing turbine, and uA is the effective flow area of the fuel pre-pressing turbine;
assuming that the fuel medium is directly drawn from the thrust chamber cooling flow path outlet 6, the flow rate of the fuel pre-compressed turbine working fuel driving the turbo pump is required to satisfy equations (3) and (4), where P is2Preloading turbine power, q, for fuelm2Preloading the turbine flow, p, for fueli2Preloading turbine inlet pressure, p, for fuele2Preloading a turbine outlet pressure, ρ, for fuel2Medium density, eta fuel pre-pressure turbine efficiency and uA fuel pre-pressure turbine effective flow area;
for driving the pre-compressed turbo pump by drawing fuel from different positions, it should be ensured that the pre-compressed turbo pump has the same power, i.e. P1＝P2From this, it is possible to obtain:
bringing (2), (4) into (5) yields:
as can be seen from equation (6), the smaller the fuel medium density is, the smaller the required drive flow rate is, under the same power condition of the pre-compression turbo pump. The fuel led out from the thrust chamber cooling flow path outlet 6 is heated by the thrust chamber 3, and compared with the fuel directly led out from the fuel main pump outlet, the fuel has higher temperature and lower density, so that the fuel of the thrust chamber cooling flow path outlet 6 has stronger working capacity than the fuel of the thrust chamber cooling flow path inlet 5, the driving flow can be reduced, and the power of the fuel pump is saved.
The cooling flow path of the injector of the thrust chamber of the afterburning cycle engine and the design method thereof can be suitable for a low-temperature full-flow afterburning cycle engine, or a fuel pre-pressurizing turbine pump 4 of the low-temperature rich afterburning cycle engine with the thrust chamber 3 cooled by fuel is driven, and an oxidant pre-pressurizing turbine pump of the low-temperature rich oxygen afterburning cycle engine with the thrust chamber 3 cooled by oxidant.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, and it is obvious for a person skilled in the art to modify the specific technical solutions described in the foregoing embodiments or to substitute part of the technical features, and these modifications or substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions protected by the present invention.
Claims (3)
1. A afterburning cycle engine thrust chamber injector cooling flow path comprises a fuel main pump (1), an oxidant main pump (2), a gas generator and a thrust chamber (3), wherein a thrust chamber cooling flow path is arranged in a chamber wall of the thrust chamber (3), and the afterburning cycle engine thrust chamber injector cooling flow path is characterized in that:
the fuel pre-pressurizing system also comprises a fuel pre-pressurizing turbine pump (4) which is coaxial with the fuel main pump (1); an outlet of the fuel main pump (1) is connected with an inlet (5) of a thrust chamber cooling flow path, an outlet (6) pipeline of the thrust chamber cooling flow path is divided into two paths, and one path of the pipeline passes through a turbine end (41) of the fuel pre-pressurizing turbine pump (4) and then leads to an injector panel of the thrust chamber (3) and is used for driving the fuel pre-pressurizing turbine pump (4) and cooling the injector panel; the other path is used for being directly connected with the inlet of the gas generator; the outlet of the oxidant main pump (2) is connected with the inlet of the gas generator;
or the system also comprises an oxidant pre-pressing turbine pump which is coaxial with the oxidant main pump (2); the outlet of the oxidant main pump (2) is connected with the inlet (5) of the thrust chamber cooling flow path, the outlet (6) pipeline of the thrust chamber cooling flow path is divided into two paths, and one path of the pipeline passes through the turbine end of the oxidant prepressing turbine pump and then leads to the injector panel of the thrust chamber (3) and is used for driving the oxidant prepressing turbine pump and cooling the injector panel; the other path is used for being directly connected with the inlet of the gas generator; the outlet of the fuel main pump (1) is connected with the inlet of the gas generator.
2. The afterburner cycle engine thrust chamber injector cooling flow path of claim 1, wherein: the gas generator is a rich gas generator (7) and/or a rich gas generator (8).
3. A method for designing a cooling flow path of an injector of a thrust chamber of an afterburner cycle engine based on the cooling flow path of the injector of the thrust chamber of the afterburner cycle engine of claim 1 or 2, comprising the steps of:
fuel is sent into a thrust chamber cooling flow path through a thrust chamber cooling flow path inlet (5) by a fuel main pump (1), the fuel sent into the thrust chamber cooling flow path is gasified and heat-exchanged at the initial stage of starting, generated gas flows out from a thrust chamber cooling flow path outlet (6) and then is divided into two paths, one path of gas does work on a turbine of a fuel pre-pressing turbine pump (4) before a fuel gas generator is ignited, the gas after the work does re-cool an injector panel of the thrust chamber (3), and the other path of gas directly flows into the fuel gas generator;
or the oxidant is sent into the thrust chamber cooling flow path through the inlet (5) of the thrust chamber cooling flow path by the oxidant main pump (2), the oxidant sent into the thrust chamber cooling flow path is gasified and heat-exchanged at the initial stage of starting, generated gas flows out from the outlet (6) of the thrust chamber cooling flow path and then is divided into two paths, one path does work on a turbine of the oxidant pre-pressing turbine pump (4) before the gas generator is ignited, the gas after the work does re-cool an injector panel of the thrust chamber (3), and the other path directly flows into the gas generator.
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| CN202011509936.9A CN112628019A (en) | 2020-12-18 | 2020-12-18 | Afterburning cycle engine thrust chamber injector cooling flow path and design method thereof |
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| CN202011509936.9A CN112628019A (en) | 2020-12-18 | 2020-12-18 | Afterburning cycle engine thrust chamber injector cooling flow path and design method thereof |
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Application publication date: 20210409 |
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