CN114810428A - Precooling device and method for engine hydrogen system under simulation verification flight state - Google Patents
Precooling device and method for engine hydrogen system under simulation verification flight state Download PDFInfo
- Publication number
- CN114810428A CN114810428A CN202210333311.4A CN202210333311A CN114810428A CN 114810428 A CN114810428 A CN 114810428A CN 202210333311 A CN202210333311 A CN 202210333311A CN 114810428 A CN114810428 A CN 114810428A
- Authority
- CN
- China
- Prior art keywords
- hydrogen
- precooling
- pump
- valve
- turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000001257 hydrogen Substances 0.000 title claims abstract description 168
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 168
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 166
- 238000012795 verification Methods 0.000 title claims abstract description 12
- 238000000034 method Methods 0.000 title claims description 13
- 238000004088 simulation Methods 0.000 title claims description 9
- 238000010992 reflux Methods 0.000 claims abstract description 28
- 239000007788 liquid Substances 0.000 claims abstract description 27
- 239000001307 helium Substances 0.000 claims abstract description 20
- 229910052734 helium Inorganic materials 0.000 claims abstract description 20
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract description 20
- 239000011261 inert gas Substances 0.000 claims abstract description 16
- 238000001816 cooling Methods 0.000 claims abstract description 13
- 238000002955 isolation Methods 0.000 claims abstract description 10
- 238000007664 blowing Methods 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 5
- 238000004364 calculation method Methods 0.000 claims description 4
- 238000012544 monitoring process Methods 0.000 claims description 4
- 238000005086 pumping Methods 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 9
- 238000007789 sealing Methods 0.000 abstract description 3
- 150000002431 hydrogen Chemical class 0.000 abstract description 2
- 238000012954 risk control Methods 0.000 abstract description 2
- 238000011084 recovery Methods 0.000 description 5
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Images
Classifications
-
- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Separation By Low-Temperature Treatments (AREA)
Abstract
A precooling device for an engine hydrogen system under a simulated verification flight state comprises a hydrogen pump front valve, a hydrogen pump, a blow-off check valve, a sonic nozzle, a hydrogen turbine, a hydrogen precooling return valve and a throttling device; pre-cooling the hydrogen pump by liquid hydrogen through a front valve of the hydrogen pump; the liquid hydrogen after passing through the hydrogen pump is divided into two paths, one path flows out through a hydrogen precooling reflux valve, and the other path flows to a hydrogen turbine; the inert gas sequentially passes through the sonic nozzle and the blow-off check valve and then is divided into two paths, one path isolates the liquid hydrogen flowing to the hydrogen turbine and flows out through the hydrogen precooling reflux valve together with the isolated liquid hydrogen, and the other path is discharged to the outside through the hydrogen turbine; the hydrogen pre-cooling reflux valve is provided with two outlets, and the throttling device is arranged on one outlet. The invention can obtain the circular precooling characteristic of the engine hydrogen system and obtain the change relation of the precooling temperature drop rate along with the blowing flow and the pressure before the pump; the safety boundary of helium isolation sealing during the circular precooling of the oxyhydrogen engine is determined, the test coverage of the engine is improved, and the risk control is facilitated.
Description
Technical Field
The invention relates to a precooling device and a precooling method for an engine hydrogen system under a simulated verification flight state, and belongs to the technical field of engines.
Background
Before the rocket is launched, the engine hydrogen system carries out circulating precooling, and liquid hydrogen from the storage tank flows back to the hydrogen storage tank after precooling an engine pipeline and a hydrogen turbopump. When the engine is subjected to ground calibration test, a discharge precooling mode is adopted, namely precooled liquid hydrogen is directly discharged, so that the circulating precooling characteristic of the engine before emission cannot be obtained, and the limit safety boundary and the safety margin of the helium isolation pressure of the dynamic seal of the hydrogen turbine pump in a real circulating precooling state cannot be obtained. The hydrogen system of the high-thrust oxyhydrogen engine is sensitive to a precooling boundary, and if the hydrogen system has no circular precooling characteristic and precooling safety margin, the situations that precooling is not successful before launching and cannot be launched, and cold hydrogen is discharged to a launching field to cause safety problems are easy to occur.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and the problem that the circulating precooling characteristic of the engine before launching cannot be obtained is solved.
The purpose of the invention is realized by the following technical scheme:
a precooling device and method of engine hydrogen system under the simulation verification flight state, 1) on the helium isolation sealing blow-off road of the test bed hydrogen turbopump, before the entrance of the blow-off check valve, set up the high coefficient of restitution sonic nozzle, under the working condition of low blow-off pressure of low-flow helium, through measuring the pressure of the entrance of the nozzle, can know the flowrate that the helium blows off accurately; 2) a two-position three-way hydrogen pre-cooling reflux valve is arranged on the test bed hydrogen pre-cooling discharge header pipe; the inlet of the hydrogen precooling reflux valve is connected with a hydrogen precooling discharge header pipe, and the pressure of a discharge port under two circulating precooling working conditions of non-pressurization and pressurization of a storage tank is simulated respectively by controlling the sections of two outlets, wherein one section is additionally provided with a flow-limiting orifice plate with a specified equivalent area; 3) a hydrogen concentration alarm is installed at the outlet of the hydrogen turbine exhaust pipe, and a wall temperature measuring point is added on the inner wall of the exhaust pipe to monitor whether the helium isolation seal of the hydrogen turbine pump leaks.
A precooling device for an engine hydrogen system under a simulated verification flight state comprises a hydrogen pump front valve, a hydrogen pump, a blow-off check valve, a sonic nozzle, a hydrogen turbine, a hydrogen precooling return valve and a throttling device;
pre-cooling the hydrogen pump by liquid hydrogen through a front valve of the hydrogen pump; the liquid hydrogen after passing through the hydrogen pump is divided into two paths, one path flows out through a hydrogen precooling reflux valve, and the other path flows to a hydrogen turbine; the inert gas sequentially passes through the sonic nozzle and the blow-off check valve and then is divided into two paths, one path isolates the liquid hydrogen flowing to the hydrogen turbine and flows out through the hydrogen precooling reflux valve together with the isolated liquid hydrogen, and the other path is discharged to the outside through the hydrogen turbine;
the hydrogen pre-cooling reflux valve is provided with two outlets, and the throttling device is arranged on one outlet.
Preferably, a turbo pump bearing is further included, the turbo pump bearing being located between the hydrogen pump and the hydrogen turbine.
Preferably, the throttling device adopts a throttling orifice plate.
Preferably, the sonic nozzle is a high-recovery coefficient sonic nozzle.
Preferably, the parameters of the high-recovery coefficient sonic nozzle structure are as follows: the inlet angle is 60-80 degrees; the length of the throat working section is about 0.5-1 times of the throat diameter; the outlet angle of the expansion section is 6-9 degrees; the length of the outlet expansion section is 20-30 times of the throat diameter.
Preferably, the throttling device determines the equivalent area of the throttling device under the ground condition through simulation calculation according to the inlet pressure of the hydrogen pump and the outlet pressure of the hydrogen precooling reflux valve under different pressurization conditions under the precooling working condition of the target field circulating pump.
A precooling method for an engine hydrogen system under a simulated verification flight state adopts the precooling device, and comprises the following steps:
controlling the pressure P1 of the front valve of the hydrogen pump by using the pressure of the hydrogen storage tank;
controlling the flow of the inert gas through the sonic nozzle;
the precooling characteristic of the engine in a precooling state is obtained by monitoring the temperature of the hydrogen pump, and the relation of the precooling temperature reduction rate along with the change of the blowing flow and the pressure before the pump is obtained;
the hydrogen precooling reflux valve respectively adopts one of the two outlets as a discharge outlet, and respectively measures the pressure of the corresponding discharge outlet; and (3) simulating the circulating precooling working condition under different pressurization states by using the pressure difference between the P1 and the pressure of the discharge port.
Preferably, a hydrogen concentration alarm instrument is installed at an outlet of the hydrogen turbine to obtain a limit safety boundary and a safety margin of the isolation pressure of the hydrogen turbine dynamic seal inert gas in a circulating precooling state.
Preferably, the flow rate of the inert gas is determined by a supersonic nozzle gas flow formula.
Preferably, the inert gas is helium.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention provides a method for simulating a real cycle precooling working condition on an arrow by using a ground discharge precooling test, which can obtain the cycle precooling characteristic of an engine hydrogen system and obtain the change relation of a precooling temperature reduction rate along with the blowing flow and the pressure before a pump; the safety boundary of helium isolation sealing during the circular precooling of the oxyhydrogen engine is determined, the test coverage of the engine is improved, the risk control is facilitated, the circular precooling test of a power system is avoided, and a large amount of research expenses are saved;
(2) according to the technical scheme, through the practical examination of rocket flight, the cyclic precooling condition simulated by the test is consistent with the practical cyclic precooling condition of the rocket power system;
(3) the high-recovery coefficient sonic nozzle can accurately obtain the helium flow under the working conditions of small-flow helium and lower blowing pressure;
(4) the equivalent area of the pore plate in the reflux valve is obtained through simulation, and the precooling working condition with the circulating pump under different pressurization conditions of the target range is accurately simulated.
Drawings
FIG. 1 is a schematic diagram of circulation precooling of a hydrogen system in a simulated flight state of ground hot trial of an engine.
Fig. 2 is a schematic diagram of a hydrogen pre-chilled return valve.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Example 1:
a pre-cooling apparatus for simulating and verifying an engine hydrogen system in a flight state, comprising: the system comprises a hydrogen pump front valve 1, a hydrogen pump 2, a blow-off one-way valve 3, a sonic nozzle 4, a hydrogen turbine 5, a hydrogen precooling reflux valve 6 and a throttle orifice 7; as shown in fig. 1.
Liquid hydrogen enters the engine through the hydrogen pump front valve 1 to pre-cool the hydrogen pump 2. The liquid hydrogen passing through the hydrogen pump 2 is divided into two paths, one path of the liquid hydrogen passes through the pump and flows out of the hydrogen precooling reflux valve 6, and the other path of the liquid hydrogen flows to the hydrogen turbine 5 through the turbine pump bearing. Helium enters the hydrogen turbine bearing through the blow-off one-way valve 3 through the sonic nozzle 4 and then is divided into two paths, one path isolates liquid hydrogen flowing to the hydrogen turbine 5, the liquid hydrogen and the liquid hydrogen flow out through the hydrogen precooling reflux valve 6, and the other path is discharged to an external field through the hydrogen turbine 5.
The pressure obtained by measuring the inlet pressure of the hydrogen pump and the outlet pressure of the hydrogen precooling reflux valve under different pressurization conditions under the precooling working condition of the target field circulating pump is obtained by simulation calculation, and the equivalent area of the throttle orifice plate 7 under the ground condition is 2.54E-4m 3 Preferably a circular hole of 18mm diameter.
The sonic nozzle 4 is preferably a high-restitution coefficient sonic nozzle.
A precooling method for an engine hydrogen system in a simulated verification flight state comprises the following steps:
the pressure P1 of the hydrogen pump front valve is controlled by the pressure of the test bed hydrogen storage tank;
the inlet of the hydrogen precooling reflux valve is connected with a 6a hydrogen precooling discharge header pipe, when the outlet of the precooling reflux valve is in a 6b state, the pressure of the discharge port is P2, and the pressure difference between the discharge port and P1 is a circulating precooling working condition when the pressure is not increased; when the outlet of the precooling reflux valve is in a 6c state, a throttle orifice plate 7 is additionally arranged at the discharge port, as shown in fig. 2, the pressure of the discharge port is controlled to be P3, and the pressure difference between the pressure of the discharge port and P1 is a circulating precooling working condition when the pressure is simulated to be increased;
the flow of helium of the blowing engine is accurately controlled through the sonic nozzle 4;
the precooling characteristic of the engine in a target range circulating precooling state is obtained by monitoring the temperature of the hydrogen pump;
and a hydrogen concentration alarm instrument is arranged at the outlet of the hydrogen turbine, and the limit safety boundary and the safety margin of the helium isolation pressure of the hydrogen turbine pump dynamic seal in the real circulation precooling state are obtained by controlling different helium flow rates, the inlet pressure of the pump front valve and the working state of the hydrogen precooling reflux valve.
Because the helium flow for isolation is small, the helium pressure before the inlet of the blowing one-way valve is low, and the high-coefficient sonic nozzle can ensure that the gas reaches the sonic velocity under the condition of low front-back pressure difference of the nozzle, so that the helium flow can be accurately calculated. The high-recovery coefficient sonic nozzle has the structural parameters as follows: 1) the inlet angle is 60-80 degrees, preferably 60 degrees; 2) the length of the throat working section is about 0.5-1 times of the throat diameter; 3) the outlet angle of the expansion section is 6-9 degrees; 4) the length of the outlet expansion section is 20-30 times of the throat diameter.
The high-coefficient sonic nozzle calculates the helium flow through a supersonic nozzle gas flow formula.
Example 2:
a precooling device for an engine hydrogen system under a simulated verification flight state comprises a hydrogen pump front valve 1, a hydrogen pump 2, a blow-off check valve 3, a sonic nozzle 4, a hydrogen turbine 5, a hydrogen precooling return valve 6 and a throttling device;
liquid hydrogen pre-cools a hydrogen pump 2 through a hydrogen pump front valve 1; the liquid hydrogen after passing through the hydrogen pump 2 is divided into two paths, one path flows out through the hydrogen precooling reflux valve 6, and the other path flows to the hydrogen turbine 5; the inert gas sequentially passes through the sonic nozzle 4 and the blow-off check valve 3 and then is divided into two paths, one path isolates the liquid hydrogen flowing to the hydrogen turbine 5, the liquid hydrogen and the isolated liquid hydrogen flow out through the hydrogen precooling reflux valve 6, and the other path is discharged to the outside through the hydrogen turbine 5;
the hydrogen pre-cooling reflux valve 6 is provided with two outlets, and a throttling device is mounted on one of the outlets.
Preferably, a turbo pump bearing is also included, which is located between the hydrogen pump 2 and the hydrogen turbine 5.
Preferably, the throttling device adopts a throttling orifice plate.
Preferably, the sonic nozzle 4 is a high-restitution coefficient sonic nozzle.
Preferably, the parameters of the high-recovery coefficient sonic nozzle structure are as follows: the inlet angle is 60-80 degrees; the length of the throat working section is about 0.5-1 times of the throat diameter; the outlet angle of the expansion section is 6-9 degrees; the length of the outlet expansion section is 20-30 times of the throat diameter.
Preferably, the throttling device determines the equivalent area of the throttling device under the ground condition through simulation calculation according to the inlet pressure of the hydrogen pump and the outlet pressure of the hydrogen precooling reflux valve under different pressurization conditions under the precooling working condition of the target field circulating pump.
A precooling method for an engine hydrogen system under a simulated verification flight state adopts the precooling device, and comprises the following steps:
controlling the pressure P1 of a front valve 1 of the hydrogen pump by using the pressure of the hydrogen storage tank;
the flow of the inert gas is controlled by the sonic nozzle 4;
the precooling characteristic of the engine in a precooling state is obtained by monitoring the temperature of the hydrogen pump 2, and the relation of the precooling temperature reduction rate along with the change of the blowing flow and the pressure before the pump is obtained;
the hydrogen precooling reflux valve 6 respectively adopts one of the two outlets as a discharge outlet, and respectively measures the pressure of the corresponding discharge outlet; and (3) simulating the circulating precooling working condition under different pressurization states by using the pressure difference between the P1 and the pressure of the discharge port.
Preferably, a hydrogen concentration alarm instrument is installed at the outlet of the hydrogen turbine 5 to obtain the limit safety boundary and the safety margin of the isolation pressure of the dynamic seal inert gas of the hydrogen turbine in the circulating precooling state.
Preferably, the flow rate of the inert gas is determined by a supersonic nozzle gas flow formula.
Preferably, the inert gas is helium.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A precooling device for an engine hydrogen system under a simulated verification flight state is characterized by comprising a hydrogen pump front valve (1), a hydrogen pump (2), a blow-off one-way valve (3), a sonic nozzle (4), a hydrogen turbine (5), a hydrogen precooling return valve (6) and a throttling device;
liquid hydrogen precools a hydrogen pump (2) through a hydrogen pump front valve (1); the liquid hydrogen after passing through the hydrogen pump (2) is divided into two paths, one path flows out through the hydrogen precooling reflux valve (6), and the other path flows to the hydrogen turbine (5); the inert gas sequentially passes through the sonic nozzle (4) and the blow-off check valve (3) and then is divided into two paths, one path isolates the liquid hydrogen flowing to the hydrogen turbine (5), the liquid hydrogen and the isolated liquid hydrogen flow out through the hydrogen precooling return valve (6), and the other path is discharged to the outside through the hydrogen turbine (5);
the hydrogen precooling reflux valve (6) is provided with two outlets, and a throttling device is arranged on one outlet.
2. The pre-cooling apparatus according to claim 1, further comprising a turbo pump bearing, the turbo pump bearing being located between the hydrogen pump (2) and the hydrogen turbine (5).
3. The pre-cooling apparatus of claim 1, wherein the throttling device is an orifice plate.
4. The pre-cooling device according to claim 1, wherein the sonic nozzle (4) is a high-restitution sonic nozzle.
5. The pre-cooling apparatus of claim 4, wherein the parameters of the high-restitution coefficient sonic nozzle structure are: the inlet angle range is 60-80 degrees; the length range of the throat working section is 0.5-1 times of the throat diameter; the outlet angle of the expansion section ranges from 6 degrees to 9 degrees; the length range of the outlet expansion section is 20-30 times of throat diameter.
6. The precooling apparatus according to claim 1, wherein the throttling device determines an equivalent area of the throttling device under the ground condition through simulation calculation according to the hydrogen pump inlet pressure and the hydrogen precooling reflux valve outlet pressure under different pressurization conditions under the precooling working condition of the shooting range circulating pump.
7. A precooling method for an engine hydrogen system under a simulation verification flight state is characterized in that the precooling device of any one of claims 1 to 6 is adopted, and comprises the following steps:
the pressure P1 of a front valve (1) of the hydrogen pump is controlled by the pressure of the hydrogen storage tank;
the flow of the inert gas is controlled by a sonic nozzle (4);
the precooling characteristic of the engine in a precooling state is obtained by monitoring the temperature of the hydrogen pump (2), and the relation of precooling temperature reduction rate with the change of blowing flow and pressure before pumping is obtained;
the hydrogen precooling reflux valve (6) respectively adopts one of the two outlets as a discharge outlet, and respectively measures the pressure of the corresponding discharge outlet; and (3) simulating the circulating precooling working condition under different pressurization states by using the pressure difference between the P1 and the pressure of the discharge port.
8. The precooling method according to claim 7, wherein a hydrogen concentration alarm is installed at an outlet of the hydrogen turbine (5) to obtain a limit safety margin and a safety margin of the inert gas isolation pressure of the dynamic seal of the hydrogen turbine in the circulating precooling state.
9. The method of precooling according to claim 7, wherein the flow rate of the inert gas is determined by a supersonic nozzle gas flow formula.
10. The method of pre-cooling of claim 7, wherein the inert gas is helium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210333311.4A CN114810428B (en) | 2022-03-30 | Precooling device and method for simulating and verifying engine hydrogen system under flight state |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210333311.4A CN114810428B (en) | 2022-03-30 | Precooling device and method for simulating and verifying engine hydrogen system under flight state |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114810428A true CN114810428A (en) | 2022-07-29 |
| CN114810428B CN114810428B (en) | 2024-05-31 |
Family
ID=
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB793689A (en) * | 1953-06-19 | 1958-04-23 | Havilland Engine Co Ltd | Rocket motors |
| RU2024777C1 (en) * | 1989-12-06 | 1994-12-15 | Андрей Федорович Кирпикин | Cryogenic liquid-propellant rocket engine |
| JPH11107858A (en) * | 1997-09-30 | 1999-04-20 | Mitsubishi Heavy Ind Ltd | Engine testing device |
| US6619031B1 (en) * | 2000-04-27 | 2003-09-16 | Vladimir V. Balepin | Multi-mode multi-propellant liquid rocket engine |
| US20040177603A1 (en) * | 2003-03-12 | 2004-09-16 | Aerojet-General Corporation | Expander cycle rocket engine with staged combustion and heat exchange |
| CN102094728A (en) * | 2010-12-30 | 2011-06-15 | 北京航空航天大学 | Supplying device of small-flow and high-temperature gas propellant |
| CN110716590A (en) * | 2019-10-18 | 2020-01-21 | 中国运载火箭技术研究院 | Liquid hydrogen storage tank pressure control system based on cryopump signal feedback |
| CN111005821A (en) * | 2019-11-29 | 2020-04-14 | 北京航天动力研究所 | Expansion cycle liquid oxygen methane upper-level engine system |
| CN111502865A (en) * | 2020-04-16 | 2020-08-07 | 西安航天动力研究所 | Test run method of open-cycle liquid oxygen kerosene engine system |
| CN213540587U (en) * | 2020-12-01 | 2021-06-25 | 陕西空天动力研究院有限公司 | Correction device for mass flow of rocket engine gas metering nozzle |
| CN114165363A (en) * | 2021-11-23 | 2022-03-11 | 北京航天动力研究所 | Thrust room test device with multi-working-condition optimization function |
| CN114198222A (en) * | 2021-12-06 | 2022-03-18 | 北京航天动力研究所 | Low-temperature displacement measuring device for turbopump rotor of liquid rocket engine |
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB793689A (en) * | 1953-06-19 | 1958-04-23 | Havilland Engine Co Ltd | Rocket motors |
| RU2024777C1 (en) * | 1989-12-06 | 1994-12-15 | Андрей Федорович Кирпикин | Cryogenic liquid-propellant rocket engine |
| JPH11107858A (en) * | 1997-09-30 | 1999-04-20 | Mitsubishi Heavy Ind Ltd | Engine testing device |
| US6619031B1 (en) * | 2000-04-27 | 2003-09-16 | Vladimir V. Balepin | Multi-mode multi-propellant liquid rocket engine |
| US20040177603A1 (en) * | 2003-03-12 | 2004-09-16 | Aerojet-General Corporation | Expander cycle rocket engine with staged combustion and heat exchange |
| CN102094728A (en) * | 2010-12-30 | 2011-06-15 | 北京航空航天大学 | Supplying device of small-flow and high-temperature gas propellant |
| CN110716590A (en) * | 2019-10-18 | 2020-01-21 | 中国运载火箭技术研究院 | Liquid hydrogen storage tank pressure control system based on cryopump signal feedback |
| CN111005821A (en) * | 2019-11-29 | 2020-04-14 | 北京航天动力研究所 | Expansion cycle liquid oxygen methane upper-level engine system |
| CN111502865A (en) * | 2020-04-16 | 2020-08-07 | 西安航天动力研究所 | Test run method of open-cycle liquid oxygen kerosene engine system |
| CN213540587U (en) * | 2020-12-01 | 2021-06-25 | 陕西空天动力研究院有限公司 | Correction device for mass flow of rocket engine gas metering nozzle |
| CN114165363A (en) * | 2021-11-23 | 2022-03-11 | 北京航天动力研究所 | Thrust room test device with multi-working-condition optimization function |
| CN114198222A (en) * | 2021-12-06 | 2022-03-18 | 北京航天动力研究所 | Low-temperature displacement measuring device for turbopump rotor of liquid rocket engine |
Non-Patent Citations (1)
| Title |
|---|
| 程谋森, 刘昆, 张育林: "液氢液氧火箭发动机预冷与启动过程数值模拟综述", 推进技术, vol. 23, no. 03, 30 June 2002 (2002-06-30), pages 177 - 181 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111006841B (en) | Wide-area air inlet pressure regulating system for hypersonic wind tunnel | |
| CN208672312U (en) | The low-temp low-pressure experimental cabin of simulated altitude | |
| CN109682924A (en) | High-pressure gas pipeline leakage lights to form injection fire test device and its test method | |
| CN111929024B (en) | Icing wind tunnel air intake and height simulation system and method | |
| CN111963337A (en) | Direct connection hot test system and hot test method for oxygen-enriched afterburning engine thrust chamber | |
| CN111122067B (en) | Gas pipeline gas leakage simulation device | |
| CN205655969U (en) | Device that leaks in simulation gas valve | |
| CN102879157A (en) | Airtightness detection method for protective engineering ventilation system and system thereof | |
| CN107782639A (en) | The back pressure test device of catalyst unit | |
| CN113340585B (en) | General test bench of fuel cell hydrogen subsystem valve body | |
| CN110749448A (en) | Supersonic engine test bed and test method thereof | |
| CN114810428B (en) | Precooling device and method for simulating and verifying engine hydrogen system under flight state | |
| CN114810428A (en) | Precooling device and method for engine hydrogen system under simulation verification flight state | |
| CN101936288B (en) | Equipment and method for test compression machine | |
| CN209655043U (en) | A kind of low-pressure fuel gas pipeline minute leakage on-line monitoring system | |
| CN109708004A (en) | A kind of low-pressure fuel gas pipeline minor leakage on-line monitoring system and method | |
| CN217111442U (en) | Gas heater test bench | |
| CN113901595B (en) | Design method for aircraft APU (auxiliary Power Unit) exhaust system in laboratory | |
| CN113175394B (en) | Hydrogen-oxygen rocket engine dynamic combustion stability identification test system and method | |
| CN211824920U (en) | Vehicle-mounted liquid hydrogen valve inner leakage detection device | |
| CN114459767B (en) | Rocket engine low-temperature supply system characteristic simulation method | |
| CN206330770U (en) | Pulse simulation device | |
| CN112577887A (en) | Water supply pipeline ambient temperature simulation test system | |
| CN106643993B (en) | Device for low-temperature test of water supply vertical pipe and water meter | |
| CN218035568U (en) | Emergency simulation platform for ammonia refrigeration system normal open and normal close valve leakage detection laboratory |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |