CN107607325B - Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method - Google Patents
Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method Download PDFInfo
- Publication number
- CN107607325B CN107607325B CN201710786811.2A CN201710786811A CN107607325B CN 107607325 B CN107607325 B CN 107607325B CN 201710786811 A CN201710786811 A CN 201710786811A CN 107607325 B CN107607325 B CN 107607325B
- Authority
- CN
- China
- Prior art keywords
- operating condition
- engine
- thrust
- engine operating
- throttle
- 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.)
- Active
Links
Landscapes
- Testing Of Engines (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
In order to solve the technical issues of existing Operating condition adjustment method is unable to satisfy pintle formula ejector filler Variable Thrust Engine job requirement, the present invention provides a kind of needles to fasten formula ejector filler Variable Thrust Engine System Operating condition adjustment method, it can ensure that entire condition range intrinsic motivation keeps higher operating condition precision, can satisfy engine operating condition required precision.Comprising steps of 1] heat mark test run before Operating condition adjustment；2] test run of engine thermal mark is carried out, the cold and hot examination difference actual value of thrust chamber is obtained；3] Operating condition adjustment after the test run of heat mark.Using method of the invention, engine operating condition precision is can be controlled within 2%, and method is simple, easy to accomplish.
Description
Technical field
The invention belongs to Aeronautics and Astronautics technical field of engines, and in particular to a kind of needle is fastened formula ejector filler change propulsive and started
Machine system condition method of adjustment.
Background technique
Variable Thrust Engine is a kind of liquid-propellant rocket engine that thrust can be continuously adjusted, and in missile armament, is visited
The deep-space detection fields such as the moon, spy fire are with a wide range of applications.But for needle fastens a wide range of Variable Thrust Engine of formula, by
It is higher in engine operating condition required precision, start eedle to fasten in addition and is had a certain difference between the cold and hot examination of formula ejector filler, and show
There is Operating condition adjustment method to be only applicable to fixed thrust needle and fasten formula ejector filler engine, due to the spray of fixed trust engine ejector filler
Geat is fixed-area, therefore existing method cannot be used for Variable Thrust Engine；In addition existing Operating condition adjustment method throttle exists
Be not mounted within when selection carried out on engine (specifically throttle individually carries out liquid flow test and selects, and pacifies again after select
Dress is on the engine), leading to the throttle size of selection, there are deviations, therefore subsequent Operating condition adjustment precision is affected, so that
Engine operating condition precision is relatively low, is unable to satisfy real work requirement, it is therefore desirable to a kind of new Operating condition adjustment method, Lai Shiying needle
Fasten the job requirement of formula ejector filler Variable Thrust Engine.
Summary of the invention
In order to solve the problems in background technique, the present invention provides a kind of needles to fasten formula ejector filler Variable Thrust Engine System
Operating condition adjustment method, it can be ensured that entire condition range intrinsic motivation keeps higher operating condition precision, can satisfy engine operating condition
Required precision.
The technical solution of the invention is as follows:
Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, comprising the following steps:
1] Operating condition adjustment before the test run of heat mark
1.1] the liquid flow test data for obtaining thrust chamber, flow regulator, cut-off valve, in conjunction with the cold and hot examination difference warp of thrust chamber
Value is tested, the parameter of throttle used in heat mark test run engine is calculated, the aperture size of throttle is calculated according to the parameter；
1.2] according to step 1.1] obtain throttle aperture size process throttle；
1.3] selection meets throttle of the engine under declared working condition:
By step 1.2] throttle that processes is respectively pivoted on engine, engine is carried out respectively in the whole of declared working condition
Machine liquid flow test, according to the design chamber pressure of the cold and hot examination difference empirical value and motor power room of the thrust chamber, selection meets hair
The throttle that motivation operating condition and mixing ratio require；
1.4] liquid flow test of the engine under remaining thrust operating condition in addition to declared working condition is carried out, carries out a not good liquor respectively
Stream is tested, and the aperture in each liquid flow test by adjusting flow regulator in engine makes when engine under forward thrust operating condition
Mixing when operating condition precision is met the requirements, and record the aperture of flow regulator at this time；
2] test run of engine thermal mark is carried out, the cold and hot examination difference actual value of thrust chamber is obtained；
3] Operating condition adjustment after the test run of heat mark
3.1] thrust chamber of engine, the liquid flow test data of flow regulator, cut-off valve are reacquired, in conjunction with step 2]
The cold and hot examination difference actual value of the thrust chamber of acquisition, the parameter of throttle used in engine after calculating heat mark test run, according to the ginseng
Number calculates the aperture size of throttle；
3.2] according to step 3.1] obtain throttle aperture size process throttle；
3.3] selection meets final throttle of the engine under declared working condition:
By step 3.2] throttle that processes is respectively pivoted on engine, and carries out engine respectively in declared working condition
Complete machine liquid flow test, according to step 2] obtain thrust chamber it is cold and hot examination difference actual value and motor power room design chamber pressure,
Selection meets the final throttle of constant engine working condition requirement；
3.4] complete machine liquid flow test, each liquid stream examination are carried out under remaining thrust operating condition in addition to declared working condition to engine
Testing the aperture by adjusting flow regulator in engine makes mixing when operating condition essence when the engine under forward thrust operating condition
Degree is met the requirements, and records the aperture of flow regulator at this time, and engine operating condition adjustment is completed.
Further, above-mentioned steps 1.1], 1.3] involved in the cold and hot examination difference empirical value of thrust chamber be oxidant road
Cold and hot examination difference empirical value Δ PxoWith the cold and hot examination difference empirical value Δ P on fuel roadxf, wherein Δ PxoTake 0.02MPa, Δ PxfIt takes
0.05MPa。
Further, above-mentioned steps 1.1] and step 3.1] in throttle parameter include throttle flow and pressure
Drop.
Further, above-mentioned steps 1.3] selection throttle method specifically:
1.3.1 process throttle installation on the engine, then by engine] is mounted on liquid flow test platform
On, adjustment makes engine inlet pressure and back-pressure meet test requirements document, records each road water flow of engine and each pressure value at this time；
1.3.2] according to step 1.3.1] water flow and pressure value that are recorded, and consider the cold and hot examination difference experience of thrust chamber
Value, propellant flow rate water flow being converted under standard inlet pressure, calculates mixing ratio and whether thrust meets the requirements, specifically
It is required that should be ± the 1% of design value for mixing ratio deviation, thrust deflexion should be ± the 2% of design value；If mixing ratio and thrust two
One of person is unsatisfactory for requiring, then re-starts test after replacing the throttle of another size, until mixing ratio and thrust all meet
Until it is required that；
The calculation method of thrust and mixing ratio is as follows:
kt=qmot/qmft (3)
Fvt=(qmot+qmft).Isv (4)
Pct=(qmot+qmft)/(qmo+qmf).Pc (5)
In above formula: qmoFor constant engine operating condition oxidant road design discharge；qmfIt is set for constant engine operating condition fuel road
Count flow；qmotFlow is adjusted for constant engine operating condition oxidant road；qmftFlow is adjusted for constant engine operating condition fuel road；
qmowMeasurement water flow is tried for constant engine operating condition oxidant road water；qmfwMeasurement water is tried for constant engine operating condition fuel road water
Flow；
PiotInlet pressure is adjusted for constant engine operating condition oxidant；PiftFor constant engine operating condition fuel road adjust into
Mouth pressure；PiowInlet pressure is tried for constant engine operating condition oxidant road water；PifwFor the examination of constant engine operating condition fuel road water
Inlet pressure；
PcFor constant engine operating condition design chamber pressure；PctFor constant engine Operating condition adjustment chamber pressure；PcwFor constant engine
Operating condition water tries back-pressure；
ΔPxoFor the cold and hot examination difference empirical value on oxidant road；ΔPxfFor the cold and hot examination difference empirical value on fuel road；
ρoFor the density of oxidant；ρfFor the density of fuel；
IsvFor the design specific impulse of constant engine operating condition；ktFor the mixing ratio adjusted value of constant engine operating condition；FvtFor hair
The thrust adjusted value of motivation declared working condition.
Preferably, above-mentioned steps 1.4] and step 3.4] in, a liquid flow test is carried out every 1000N or 500N.
Further, above-mentioned steps 3.3] in selection throttle method specifically:
kt=qmot/qmft；
Fvt=(qmot+qmft)·I′sv；
Pct=(qmot+qmft)/(q′mo+q′mf)·P′c
In above formula: q 'moFor constant engine operating condition oxidant road heat mark flow；q′mfFor constant engine operating condition fuel road
Heat mark flow；qmotFlow is adjusted for constant engine operating condition oxidant road；qmftIt adjusts and flows for constant engine operating condition fuel road
Amount；qmowMeasurement water flow is tried for constant engine operating condition oxidant road water；qmfwIt tries to survey for constant engine operating condition fuel road water
Measure water flow；
PiotInlet pressure is adjusted for constant engine operating condition oxidant road；PiftFor the adjustment of constant engine operating condition fuel road
Inlet pressure；PiowInlet pressure is tried for constant engine operating condition oxidant road water；PifwFor constant engine operating condition fuel road water
Try inlet pressure；
P′cFor constant engine operating condition heat mark chamber pressure；PctFor constant engine Operating condition adjustment chamber pressure；PcwFor constant engine
Operating condition water tries back-pressure；
ΔP′xoFor the cold and hot examination difference actual value on oxidant road；ΔP′xfFor the cold and hot examination difference actual value on fuel road；
ρoFor the density of oxidant；ρfFor the density of fuel；
I′svFor the practical specific impulse of heat mark test run measurement under constant engine operating condition；ktFor the mixing of constant engine operating condition
Compare adjusted value；FvtFor the thrust adjusted value of constant engine operating condition.
Advantages of the present invention:
Using method of the invention, engine operating condition precision is can be controlled within 2%, and method is simple, easy to accomplish, energy
Enough meet the requirement of Variable Thrust Engine operating condition precision；Method of the invention, which is applicable not only to needle, fastens formula ejector filler change propulsive and starts
The Operating condition adjustment of machine can also be applied to the Operating condition adjustment that needle fastens the fixed trust engine of formula ejector filler.
Detailed description of the invention
Fig. 1 is Operating condition adjustment method flow block diagram of the invention.
Specific embodiment
It elaborates below in conjunction with the drawings and specific embodiments to the present invention.
Embodiment:
In the present embodiment, engine operating condition variation range is 7500N~1500N, declared working condition 7500N.5000N~
1500N is other cavitation operating conditions (remaining thrust operating condition i.e. described in the present invention), and thrust interval takes 1000N.
It is specific as follows that needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method:
1] Operating condition adjustment before the test run of heat mark
1.1] the liquid flow test data for obtaining thrust chamber, flow regulator, cut-off valve, in conjunction with the cold and hot examination difference warp of thrust chamber
Value is tested, the parameter of throttle used in heat mark test run engine is calculated, the aperture size of throttle is calculated according to the parameter；Throttling
The parameter of circle includes flow and pressure drop；
1.2] according to step 1.1] obtain throttle aperture size process throttle；
1.3] selection meets throttle of the engine under maximum thrust operating condition:
By step 1.2] throttle that processes is respectively pivoted on engine, engine is carried out respectively in the whole of declared working condition
Machine liquid flow test, according to the design chamber pressure of the cold and hot examination difference empirical value and motor power room of the thrust chamber, selection meets hair
The throttle that motivation operating condition and mixing ratio require；Specifically:
1.3.1 process throttle installation on the engine, then by engine] is mounted on liquid flow test platform
On, adjustment makes engine inlet pressure and back-pressure meet test requirements document, records each road water flow of engine and each pressure value at this time；
1.3.2] according to step 1.3.1] water flow and pressure value that are recorded, and consider the cold and hot examination difference experience of thrust chamber
Value, propellant flow rate water flow being converted under standard inlet pressure, calculates mixing ratio and whether thrust meets the requirements, specifically
It is required that should be ± the 1% of design value for mixing ratio deviation, thrust deflexion should be ± the 2% of design value；If mixing ratio and thrust two
One of person is unsatisfactory for requiring, then re-starts test after replacing the throttle of another size, until mixing ratio and thrust all meet
Until it is required that；
The calculation method of thrust and mixing ratio is as follows:
kt=qmot/qmft (3)
Fvt=(qmot+qmft).Isv (4)
Pct=(qmot+qmft)/(qmo+qmf).Pc (5)
In above formula: qmoFor constant engine operating condition oxidant road design discharge；qmfIt is set for constant engine operating condition fuel road
Count flow；qmotFlow is adjusted for constant engine operating condition oxidant road；qmftFlow is adjusted for constant engine operating condition fuel road；
qmowMeasurement water flow is tried for constant engine operating condition oxidant road water；qmfwMeasurement water is tried for constant engine operating condition fuel road water
Flow；
PiotInlet pressure is adjusted for constant engine operating condition oxidant road；PiftFor the adjustment of constant engine operating condition fuel road
Inlet pressure；PiowInlet pressure is tried for constant engine operating condition oxidant road water；PifwFor constant engine operating condition fuel road water
Try inlet pressure；
PcFor constant engine operating condition design chamber pressure；PctFor constant engine Operating condition adjustment chamber pressure；PcwFor constant engine
Operating condition water tries back-pressure；
ΔPxoFor the cold and hot examination difference empirical value on oxidant road, 0.02MPa is taken；ΔPxfFor the cold and hot examination difference on fuel road
Empirical value takes 0.05MPa；
ρoFor the density of oxidant；ρfFor the density of fuel；
IsvFor the design specific impulse of constant engine operating condition；ktFor the mixing ratio adjusted value of constant engine operating condition；IsvFor hair
The specific impulse of motivation declared working condition；FvtFor the thrust adjusted value of constant engine operating condition.
1.4] to engine under remaining thrust operating condition in addition to declared working condition, a liquid flow test is carried out every 1000N,
Aperture in each liquid flow test by adjusting flow regulator in engine makes the mixing when engine under forward thrust operating condition
When operating condition precision is met the requirements, and records the aperture of flow regulator at this time；
2] test run of engine thermal mark is carried out, the cold and hot examination difference actual value of thrust chamber is obtained；
3] Operating condition adjustment after the test run of heat mark
3.1] thrust chamber of engine, the liquid flow test data of flow regulator, cut-off valve are reacquired, in conjunction with step 2]
The cold and hot examination difference actual value of the thrust chamber of acquisition, the parameter of throttle used in engine after calculating heat mark test run, according to this meter
The throttle parameter of calculation calculates the aperture size of throttle；
3.2] according to step 3.1] obtain throttle aperture size process throttle；
3.3] selection meets final throttle of the engine under maximum thrust operating condition:
By step 3.2] throttle that processes is respectively pivoted on engine, and carries out engine respectively in declared working condition
Complete machine liquid flow test, according to step 2] obtain thrust chamber it is cold and hot examination difference actual value and motor power room design chamber pressure,
Selection meets the final throttle of constant engine working condition requirement；Specific method is with step 1.3.1] -1.3.2], only calculating
When by the constant engine operating condition oxidant road design discharge q in above-mentioned formula (1)-(5)moWith constant engine operating condition oxidant
Road heat mark flow q 'moReplacement, by constant engine operating condition fuel road design discharge qmfWith constant engine operating condition fuel road heat mark
Flow q 'mfReplacement, by constant engine operating condition design chamber pressure PcWith constant engine operating condition heat mark chamber pressure P 'cReplacement, will aoxidize
The cold and hot examination difference empirical value Δ P on agent roadxoWith the cold and hot examination difference actual value Δ P ' on oxidant roadxoReplacement, by the cold of fuel road
Heat examination difference empirical value Δ PxfWith the cold and hot examination difference actual value Δ P ' on fuel roadxfReplacement, by the design of constant engine operating condition
Specific impulse IsvWith the practical specific impulse I ' of heat mark test run measurement under constant engine operating conditionsvReplacement.
3.4] to engine under remaining thrust operating condition in addition to declared working condition, a complete machine liquid stream is carried out every 1000N
It tests, by adjusting the aperture of flow regulator in engine in each liquid flow test, makes when the engine under forward thrust operating condition
Mixing when operating condition precision is met the requirements, and record the aperture of flow regulator at this time；Engine operating condition adjustment is completed.
To engine test run again after being adjusted using the above method, the precision of obtained mixing ratio and thrust is shown in Table 1, table 2.
1 mixing ratio Adjustment precision of table compares
2 thrust Adjustment precision of table compares
It can be seen that using method of the invention from above-mentioned Tables 1 and 2 to pintle formula ejector filler Variable Thrust Engine System
After the completion of Operating condition adjustment, test run mixing ratio deviation is -0.24%~+0.91%, far smaller than ± the 1% of design requirement again；
Thrust deflexion is 0.73%~1.72%, less than ± the 2% of design requirement, can satisfy the real work requirement of engine.
Claims (6)
1. needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, which comprises the following steps:
1] Operating condition adjustment before the test run of heat mark
1.1] the liquid flow test data for obtaining thrust chamber, flow regulator, cut-off valve, in conjunction with the cold and hot examination difference experience of thrust chamber
Value calculates the parameter of throttle used in heat mark test run engine, the aperture size of throttle is calculated according to the parameter；
1.2] according to step 1.1] obtain throttle aperture size process throttle；
1.3] selection meets throttle of the engine under maximum thrust operating condition:
By step 1.2] throttle that processes is respectively pivoted on engine, carries out engine respectively and try in the liquid stream of declared working condition
It tests, according to the design chamber pressure of the cold and hot examination difference empirical value and motor power room of the thrust chamber, selection meets engine operating condition
The throttle required with mixing ratio；
1.4] to engine under remaining thrust operating condition in addition to declared working condition, a liquid flow test, each liquid stream are carried out respectively
Aperture in test by adjusting flow regulator in engine makes the mixing of the engine under the forward thrust operating condition when operating condition
Precision is met the requirements, and records the aperture of flow regulator at this time；
2] test run of engine thermal mark is carried out, the cold and hot examination difference actual value of thrust chamber is obtained；
3] Operating condition adjustment after the test run of heat mark
3.1] thrust chamber of engine, the liquid flow test data of flow regulator, cut-off valve are reacquired, in conjunction with step 2] it obtains
The cold and hot examination difference actual value of thrust chamber, the parameter of throttle used in engine after heat mark test run is calculated, according to the parameter meter
Calculate the aperture size of throttle；
3.2] according to step 3.1] obtain throttle aperture size process throttle；
3.3] selection meets final throttle of the engine under maximum thrust operating condition:
By step 3.2] throttle that processes is respectively pivoted on engine, and carries out engine respectively in the liquid stream of declared working condition
Test, according to step 2] obtain thrust chamber it is cold and hot examination difference actual value and motor power room design chamber pressure, selection meet
The final throttle of constant engine working condition requirement；
3.4] liquid flow test is carried out under remaining thrust operating condition in addition to declared working condition to engine, passed through in each liquid flow test
The aperture of flow regulator makes the mixing of the engine under the forward thrust operating condition when operating condition precision satisfaction is wanted in adjustment engine
It asks, and records the aperture of flow regulator at this time, engine operating condition adjustment is completed.
2. needle according to claim 1 fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, which is characterized in that
The step 1.1], 1.3] involved in thrust chamber it is cold and hot examination difference empirical value be oxidant road cold and hot examination difference empirical value Δ
PxoWith the cold and hot examination difference empirical value Δ P on fuel roadxf, wherein Δ PxoTake 0.02MPa, Δ PxfTake 0.05MPa.
3. needle according to claim 1 fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, which is characterized in that
The step 1.1] and step 3.1] in throttle parameter include throttle flow and pressure drop.
4. needle according to claim 1 fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, which is characterized in that
The step 1.3] selection throttle method specifically:
1.3.1] process throttle installation on the engine, then by engine is mounted on liquid flow test platform, is adjusted
It is whole that engine inlet pressure and back-pressure is made to meet test requirements document, record each road water flow of engine and each pressure value at this time；
1.3.2] according to step 1.3.1] water flow and pressure value that are recorded, and consider the cold and hot examination difference empirical value of thrust chamber,
Propellant flow rate water flow being converted under standard inlet pressure, calculates mixing ratio and whether thrust meets the requirements, and specifically wants
Should be design value for mixing ratio deviation ± 1% is sought, thrust deflexion should be ± the 2% of design value；If both mixing ratio and thrust
One of be unsatisfactory for requiring, then re-start test after replacing the throttle of another size, wanted until mixing ratio and thrust all meet
Until asking；
The calculation method of thrust and mixing ratio is as follows:
kt=qmot/qmft (3)
Fvt=(qmot+qmft).Isv (4)
Pct=(qmot+qmft)/(qmo+qmf).Pc (5)
In above formula: qmoFor constant engine operating condition oxidant road design discharge；qmfIt designs and flows for constant engine operating condition fuel road
Amount；qmotFlow is adjusted for constant engine operating condition oxidant road；qmftFlow is adjusted for constant engine operating condition fuel road；qmow
Measurement water flow is tried for constant engine operating condition oxidant road water；qmfwMeasurement water flow is tried for constant engine operating condition fuel road water
Amount；
PiotInlet pressure is adjusted for constant engine operating condition oxidant road；PiftEntrance is adjusted for constant engine operating condition fuel road
Pressure；PiowInlet pressure is tried for constant engine operating condition oxidant road water；PifwFor constant engine operating condition fuel road water try into
Mouth pressure；
PcFor constant engine operating condition design chamber pressure；PctFor constant engine Operating condition adjustment chamber pressure；PcwFor constant engine operating condition
Water tries back-pressure；
ΔPxoFor the cold and hot examination difference empirical value on oxidant road；ΔPxfFor the cold and hot examination difference empirical value on fuel road；
ρoFor the density of oxidant；ρfFor the density of fuel；
IsvFor the design specific impulse of constant engine operating condition；ktFor the mixing ratio adjusted value of constant engine operating condition；FvtFor engine
The thrust adjusted value of declared working condition.
5. needle according to claim 1 fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, which is characterized in that
The step 1.4] and step 3.4] in, a liquid flow test is carried out every 1000N or 500N.
6. needle according to claim 1 fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method, which is characterized in that
The step 3.3] in selection throttle method specifically:
kt=qmot/qmft；
Fvt=(qmot+qmft)·I′sv；
Pct=(qmot+qmft)/(q′mo+q′mf)·P′c
In above formula: q 'moFor constant engine operating condition oxidant road heat mark flow；q′mfFor constant engine operating condition fuel road heat mark
Flow；qmotFlow is adjusted for constant engine operating condition oxidant road；qmftFlow is adjusted for constant engine operating condition fuel road；
qmowMeasurement water flow is tried for constant engine operating condition oxidant road water；qmfwMeasurement water is tried for constant engine operating condition fuel road water
Flow；
PiotInlet pressure is adjusted for constant engine operating condition oxidant road；PiftEntrance is adjusted for constant engine operating condition fuel road
Pressure；PiowInlet pressure is tried for constant engine operating condition oxidant road water；PifwFor constant engine operating condition fuel road water try into
Mouth pressure；
P′cFor constant engine operating condition heat mark chamber pressure；PctFor constant engine Operating condition adjustment chamber pressure；PcwFor constant engine operating condition
Water tries back-pressure；
ΔP′xoFor the cold and hot examination difference actual value on oxidant road；ΔP′xfFor the cold and hot examination difference actual value on fuel road；
ρoFor the density of oxidant；ρfFor the density of fuel；
I′svFor the practical specific impulse of heat mark test run measurement under constant engine operating condition；ktFor the mixing ratio tune of constant engine operating condition
Whole value；FvtFor the thrust adjusted value of constant engine operating condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710786811.2A CN107607325B (en) | 2017-09-04 | 2017-09-04 | Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710786811.2A CN107607325B (en) | 2017-09-04 | 2017-09-04 | Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107607325A CN107607325A (en) | 2018-01-19 |
| CN107607325B true CN107607325B (en) | 2019-04-23 |
Family
ID=61056119
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710786811.2A Active CN107607325B (en) | 2017-09-04 | 2017-09-04 | Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107607325B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2774006C1 (en) * | 2021-07-16 | 2022-06-14 | Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" | Method for monitoring the technical condition of a liquid rocket engine |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780444B (en) * | 2021-01-26 | 2021-11-02 | 西安航天动力研究所 | Shutdown processing method for normal-temperature propellant pin-bolt type engine anti-cavity-crossing |
| CN114577463B (en) * | 2022-05-05 | 2022-08-12 | 西安航天动力研究所 | Reliability evaluation method of bolt injector |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101418737B (en) * | 2007-10-22 | 2011-06-29 | 赵华 | Method for controlling air input of engine by intake pressure sensor signal |
| CN101865143B (en) * | 2010-07-08 | 2012-05-23 | 中国航天科技集团公司第六研究院第十一研究所 | Device for automatically adjusting power of turbine pump |
| CN103278330A (en) * | 2013-04-24 | 2013-09-04 | 北京航天试验技术研究所 | Propellant flow comparison and measurement system for attitude and orbit control engine testing platform |
| CN104358625B (en) * | 2014-07-11 | 2016-05-18 | 中国航天科技集团公司第六研究院第十一研究所 | The method of a kind of Variable Thrust Engine thrust closed-loop control |
| CN104483135B (en) * | 2014-12-03 | 2017-06-06 | 中国人民解放军国防科学技术大学 | A kind of liquid-propellant rocket engine defective pipe partition method |
| CN105863882B (en) * | 2016-04-27 | 2017-09-12 | 北京航空航天大学 | A kind of flow for high-strength hydrogen peroxide change propulsive solid-liquid rocket positions adjustable DC ejector filler |
-
2017
- 2017-09-04 CN CN201710786811.2A patent/CN107607325B/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2774006C1 (en) * | 2021-07-16 | 2022-06-14 | Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" | Method for monitoring the technical condition of a liquid rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107607325A (en) | 2018-01-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107607325B (en) | Needle fastens formula ejector filler Variable Thrust Engine System Operating condition adjustment method | |
| Koupper et al. | Development of an engine representative combustor simulator dedicated to hot streak generation | |
| Welsh et al. | RDE integration with T63 turboshaft engine components | |
| US10330023B2 (en) | Fuel flow estimation and control system and method in a gas turbine engine | |
| US11365683B2 (en) | Fuel supply control device | |
| EP3348810B1 (en) | Injection cooled cooling air system for a gas turbine engine and a corresponding method | |
| EP2925984B1 (en) | Method and arrangement for controlling fuel supply for a gas turbine | |
| Koupper | Unsteady multi-component simulations dedicated to the impact of the combustion chamber on the turbine of aeronautical gas turbines | |
| US11208959B2 (en) | System and method for flexible fuel usage for gas turbines | |
| US11927141B2 (en) | Method for determining the density of fuel for metering fuel in a fuel supply circuit of an aircraft engine | |
| Bedard et al. | Student design/build/test of a throttleable LOX-LCH4 thrust chamber | |
| CN113157010B (en) | Method and device for regulating and controlling thrust of deep variable thrust engine and electronic equipment | |
| Randall et al. | Numerical and experimental study of heat transfer in a rotating detonation engine | |
| Meyer et al. | Experimental characterization of heat transfer coefficients in a rotating detonation engine | |
| CN104919160A (en) | Gas turbine fuel supply method and arrangement | |
| Zhao et al. | Coupling characteristic analysis and propagation direction control in hydrogen–air rotating detonation combustor with turbine | |
| Fievisohn et al. | Closed loop integration of a rotating detonation combustor in a T63 gas turbine engine | |
| RU2555429C2 (en) | Method and device to generate signal of setting point | |
| Shine et al. | Influence of coolant injector configuration on film cooling effectiveness for gaseous and liquid film coolants | |
| Shepard et al. | Effects of Inlet Area Ratio on Operability of an Axial Air Inlet Rotating Detonation Combustor | |
| Cataldi et al. | Influence of high fogging systems on gas turbine engine operation and performance | |
| CN103968907A (en) | Method and device for measuring supercritical and gaseous hydrocarbon fuel dense flow | |
| He et al. | NOx emissions performance and correlation equations for a multipoint LDI injector | |
| Cataldi et al. | Influence of high fogging systems on gas turbine engine operation and performance | |
| US20170074173A1 (en) | Control system and method of controlling a variable area gas turbine engine |
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 | ||
| GR01 | Patent grant |