CN108182297A - Rocket chamber's method for analyzing efficiency and system - Google Patents

Rocket chamber's method for analyzing efficiency and system Download PDF

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Publication number
CN108182297A
CN108182297A CN201710766220.9A CN201710766220A CN108182297A CN 108182297 A CN108182297 A CN 108182297A CN 201710766220 A CN201710766220 A CN 201710766220A CN 108182297 A CN108182297 A CN 108182297A
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engine
throat
temperature
chamber
oxidant
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CN108182297B (en
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杨成虎
林庆国
张志远
刘昌国
刘犇
赵婷
姚锋
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Shanghai Institute of Space Propulsion
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation

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  • General Engineering & Computer Science (AREA)
  • Pure & Applied Mathematics (AREA)
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  • Testing Of Engines (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Abstract

The invention discloses a kind of rocket chamber's method for analyzing efficiency and systems, this method is used considers engine combustion chamber pressure simultaneously when burner efficiency calculates, oxidant and fuel flow rate, throat's temperature data, using the identical average value in interval after each parameter stability, and throat diameter during using throat's mean temperature amendment work, using revised throat diameter and chamber pressure, oxidant and fuel flow rate calculate actual characteristic speed, theoretical characteristic velocity is calculated using the chamber pressure average value and mixing ratio in same section, and then calculate burner efficiency.The present invention more accurately realizes the analysis of burner efficiency, and more accurately foundation is provided for the comparison of the Performance Evaluation of same Different Work Condition of Engine and different engines.

Description

Rocket chamber's method for analyzing efficiency and system
Technical field
The present invention relates to rocket engine fields, and in particular to a kind of rocket chamber's method for analyzing efficiency and is System.
Background technology
Burner efficiency is the important parameter of engine performance assessment, during reseach of engine, is needed by starting Machine heat run is examined, and obtains the burner efficiency and nozzle efficiency of engine, and the wherein acquisition of nozzle efficiency is based on engine ratio Punching and burner efficiency are calculated, therefore accurate acquisition engine chamber efficiency, for accurate evaluation engine performance, change Into or determining engine design it is all extremely important.
At present in engine thermal test run, burner efficiency can not directly measure to obtain, but by being surveyed before test run Engine throat diameter is measured, the parameters such as chamber pressure and propellant flow rate are measured in commissioning process, then by following formula It is calculated：
In terms of calculation formula, burner efficiency is not related with engine operating temperature.But since material expands with heat and contract with cold effect Should, when real engine works, throat's temperature reaches 1000 DEG C or more, and throat diameter at this moment is generally more than room temperature before test run The diameter value of lower measurement causes the propellant flow rate for generating identical chamber pressure bigger than normal before relatively expanding, therefore as stated above The burner efficiency of acquisition is generally less than actual value, it is assumed that throat's temperature reaches 1200 DEG C, linear expansion coefficient 8e-6/ DEG C, traditionally calculating can cause result to deviate actual value close to 2%.On the other hand, throat's temperature is steady when engine works The stabilization time fixed time generally compared with flow and pressure is long, and before throat's temperature is stablized, combustion chamber throat diameter is also changing, The burner efficiency that this stage obtains is nor actual value.Notice the combustion that throat's temperature is higher, and conventional method is calculated It burns room efficiency and deviates that actual value is bigger, and then causes the nozzle efficiency being calculated based on burner efficiency also inclined by same ratio From actual value.Therefore, same engine because operating mode difference cause operating temperature different or different engine operating temperatures not Meanwhile the burner efficiency and nozzle efficiency of conventional method acquisition can not truly react difference therein, so as to mislead hair The improvement and confirmation of motivation design point.
Invention content
For solve it is above-mentioned in the prior art the defects of, the present invention provides a kind of efficiency analysis sides of rocket chamber Method and system provide accurate foundation for the comparison of the Performance Evaluation of same Different Work Condition of Engine and different engines.
The purpose of the present invention is achieved through the following technical solutions：A kind of rocket chamber's efficiency analysis system, Including
Data acquisition module, for carrying out room temperature T0Lower engine throat diameter Dt0, the expansion of corresponding combustor material line Engine combustion chamber pressure P when factor alpha, engine thermal test runc(t), oxidant and fuel mass flow rates qmo(t) and qmf(t) And throat temperature Tt(t) acquisition；
Statistical average computing module for carrying out the acquisition of each mean parameter of engine by preset algorithm, obtains To chamber pressure average valueOxidant and fuel mass flow rates average valueWithThroat's temperature averages
Throat diameter computing module, for according to preset formula：Carry out engine Throat diameter D during worktCalculating；Wherein, α is the linear expansion coefficient of combustion chamber base material at the corresponding temperature；
Mixing ratio computing module, for according to preset formula：Mixing ratioCarry out oxidant and The fuel stream Measure mixing ratio rmCalculating；
Actual characteristic speed calculation module, for for according to preset formula：It carries out practical Characteristic velocity C*Calculating；Wherein, DtFor the throat diameter after temperature adjustmemt；
Theoretical characteristic velocity computing module, utilizes chamber pressureWith mixing ratio rm, by minimum Gibbs free energy original Reason calculates theoretical characteristic velocity
Engine chamber efficiency calculation module, for passing through preset formulaCarry out engine chamber effect Rate ηcCalculating.
The present invention also provides a kind of rocket chamber's method for analyzing efficiencies, include the following steps：
Step 1 passes through data collecting module collected room temperature T0Lower engine throat diameter Dt0, and inquire corresponding combustion chamber Linear expansion coefficient α；
Step 2 carries out engine thermal test run, passes through data collecting module collected engine combustion chamber pressure Pc(t), it aoxidizes Agent and fuel mass flow rates qmo(t) and qmf(t), throat's temperature Tt(t)；
Step 3, by statistical average computing module, to engine, each parameter takes arithmetic mean of instantaneous value, obtains chamber pressure Average valueOxidant and fuel mass flow rates average valueWithThroat's temperature averages
Step 4, using throat's temperature averages, the throat calculated by throat diameter computing module when engine works is straight Diameter Dt：
Wherein, α is the linear expansion coefficient of combustion chamber base material at the corresponding temperature；
And according to oxidant and fuel flow rate average value, mixing ratio r is calculated by mixing ratio computing modulem：
Step 5 calculates actual characteristic speed C by actual characteristic speed calculation module*：
Wherein, DtFor the throat diameter after temperature adjustmemt；
Step 6 utilizes chamber pressureWith mixing ratio rm, minimum gibbs is pressed by theoretical characteristic velocity computing module Free energy principle calculates theoretical characteristic velocity
Step 7 calculates engine chamber efficiency eta by engine chamber efficiency calculation modulec：
Wherein, the throat diameter after the temperature adjustmemt is calculated using linear expansion coefficientIt is average to ensure that parameter is derived from identical engine condition when being averaged to each parameter Value computation interval is same time interval, when averaging to parameter during engine test, it is desirable that test program length energy Ensure that the parameters such as chamber pressure, oxidant and fuel flow rate, throat's temperature there are enough stable sections, stablize segment length and be not less than 5s。
Compared with prior art, the invention has the advantages that：
It is higher than punching performance in order to obtain in engine design, tissue is needed more fully to burn, is generated higher On the other hand temperature, in order to reduce the requirement to heat-resisting material, and wishes that the lower engine operating temperature the better.Therefore it needs Engine operating temperature is reduced as possible under the premise of engine performance is not influenced, combustion chamber effect during by short jet pipe test run Rate assesses engine performance.It, can be to higher according to Such analysis it is found that if do not considered influence of the temperature to combustion chamber throat diameter At a temperature of engine performance underestimate, so as to designing engine cooling to form erroneous judgement, causing can only be in full-scale height later Relatively low engine/motor specific impulse performance is obtained during sky simulation heat run.Pass through the burner efficiency analysis method of the present invention, Neng Gou Short jet pipe examines the stage, considers the influence accurate evaluation engine performance of temperature, saves significantly on research fund and period.
Description of the drawings
Fig. 1 is engine throat diameter change schematic diagram in the embodiment of the present invention.
Fig. 2 is engine operating parameter curve graph in the embodiment of the present invention.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following embodiment will be helpful to the technology of this field Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this field For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention Protection domain.In the description of the present invention, it is to be understood that term " on ", " under ", "front", "rear", "left", "right", The orientation or position relationship of the instructions such as " vertical ", " level ", " top ", " bottom ", " interior ", " outer " be based on orientation shown in the drawings or Position relationship is for only for ease of the description present invention and simplifies description rather than instruction or imply that signified device or element must There must be specific orientation, with specific azimuth configuration and operation, therefore be not considered as limiting the invention.
An embodiment of the present invention provides a kind of rocket chamber's efficiency analysis system, including
Data acquisition module, for carrying out room temperature T0Lower engine throat diameter Dt0, the expansion of corresponding combustor material line Engine combustion chamber pressure P when factor alpha, engine thermal test runc(t), oxidant and fuel mass flow rates qmo(t) and qmf(t) And throat temperature Tt(t) acquisition；
Statistical average computing module for carrying out the acquisition of each mean parameter of engine by preset algorithm, obtains To chamber pressure average valueOxidant and fuel mass flow rates average valueWithThroat's temperature averages
Throat diameter computing module, for according to preset formula：Carry out engine Throat diameter D during worktCalculating；Wherein, α is the linear expansion coefficient of combustion chamber base material at the corresponding temperature；
Mixing ratio computing module, for according to preset formula：Mixing ratioCarry out oxidant and The fuel stream Measure mixing ratio rmCalculating；
Actual characteristic speed calculation module, for for according to preset formula：It carries out practical Characteristic velocity C*Calculating；Wherein, DtFor the throat diameter after temperature adjustmemt；
Theoretical characteristic velocity computing module, utilizes chamber pressureWith mixing ratio rm, by minimum Gibbs free energy original Reason calculates theoretical characteristic velocity
Engine chamber efficiency calculation module, for passing through preset formulaCarry out engine chamber effect Rate ηcCalculating.Throat diameter after the temperature adjustmemt is calculated using linear expansion coefficientIt is average to ensure that parameter is derived from identical engine condition when being averaged to each parameter Value computation interval is same time interval, when averaging to parameter during engine test, it is desirable that test program length energy Ensure that the parameters such as chamber pressure, oxidant and fuel flow rate, throat's temperature there are enough stable sections, stablize segment length and be not less than 5s。
Fig. 1 is engine chamber type face in the operating condition relative to the change schematic diagram of normal temperature state.Solid line in figure Part is room temperature lower combustion chamber type face, before on-test, can measure environment temperature T0Lower throat diameter Dt0.Dotted line is work shape The expansion of state lower combustion chamber generates the state after radial and axial displacement, and throat diameter is D in figure after expansiont。
Fig. 2 is the engine combustion chamber pressure measured in experiment, propellant flow rate and throat's temperature curve, for the ease of same When show, throat's temperature is drawn in 0.1 ratio of actual parameter, and pressure data is by the draftings of 10 times of ratios of actual parameter.Take two void It is straight that throat is calculated according to throat temperature averages bond material linear expansion coefficient α in each parameter stability section average value between line Diameter is
Combustion chamber features speed and burner efficiency are calculated using the throat diameter of working condition.
Embodiment
By taking certain engine chamber efficiency analysis as an example,
Step 1 passes through data collecting module collected engine room temperature T0Throat diameter D under (25 DEG C)t0=18.00mm, And α=6e-6/ DEG C of query material linear expansion coefficient.
By data collecting module collected data when step 2, engine test, relevant parameter curve as shown in Fig. 2, according to Test run parameter curve (Fig. 2), each parameter of engine reach stable after 40s, take 40s~48s sections (two vertical dotted lines in figure Between) parameter；
Step 3 carries out mean value calculation as parameter of the statistical average computing module to obtained by, obtains throat's temperature and puts down Mean valueOxidizer flow rate average valueFuel flow rate average valueBurning chamber pressure Power average value
Step 4 passes through the larynx under throat diameter computing module progress engine behavior according to throat's temperature averages The calculating of portion's diameter：
Dt=18.00* (1+6e-6* (1612-25))=18.23mm
Step 5 calculates mixing ratio according to oxidant and fuel flow rate average value by mixing ratio computing module：
rm=93.2/56.6=1.647
Step 6, the throat diameter according under engine behavior, chamber pressure, oxidant and fuel flow rate, pass through Actual characteristic speed calculation module calculates engine actual characteristic speed：
Step 7, according to engine mixture ratio and chamber pressure, pass through theoretical characteristic velocity computing module and calculate engine Theoretical characteristic velocity：
C*=1742m/s
Step 8 calculates engine chamber efficiency by engine chamber efficiency calculation module：
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited in above-mentioned Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow Ring the substantive content of the present invention.

Claims (5)

1. a kind of rocket chamber's efficiency analysis system, which is characterized in that including
Data acquisition module, for carrying out room temperature T0Lower engine throat diameter Dt0, corresponding combustor material linear expansion coefficient Engine combustion chamber pressure P when α, engine thermal test runc(t), oxidant and fuel mass flow rates qmo(t) and qmf(t) and Throat temperature Tt(t) acquisition；
Statistical average computing module for carrying out the acquisition of each mean parameter of engine by preset algorithm, is fired Burn chamber pressure average valueOxidant and fuel mass flow rates average valueWithThroat's temperature averages
Throat diameter computing module, for according to preset formula：Carry out engine work When throat diameter DtCalculating；Wherein, α is the linear expansion coefficient of combustion chamber base material at the corresponding temperature；
Mixing ratio computing module, for according to preset formula：Mixing ratioIt carries out oxidant and fuel flow rate mixes Composition and division in a proportion rmCalculating；
Actual characteristic speed calculation module, for for according to preset formula：Carry out actual characteristic Speed C*Calculating；Wherein, DtFor the throat diameter after temperature adjustmemt；
Theoretical characteristic velocity computing module, utilizes chamber pressureWith mixing ratio rm, calculated by minimum Gibbs free energy principle Theoretical characteristic velocity
Engine chamber efficiency calculation module, for passing through preset formulaCarry out engine chamber efficiency etac's It calculates.
2. a kind of rocket chamber's method for analyzing efficiency, which is characterized in that include the following steps：
Step 1 passes through data collecting module collected room temperature T0Lower engine throat diameter Dt0, and inquire corresponding combustor material Linear expansion coefficient α；
Step 2 carries out engine thermal test run, passes through data collecting module collected engine combustion chamber pressure Pc(t), oxidant and Fuel mass flow rates qmo(t) and qmf(t), throat's temperature Tt(t)；
Step 3, by statistical average computing module, to engine, each parameter takes arithmetic mean of instantaneous value, obtains chamber pressure and is averaged ValueOxidant and fuel mass flow rates average valueWithThroat's temperature averages
Step 4, using throat's temperature averages, throat diameter D when engine works is calculated by throat diameter computing modulet：
Wherein, α is the linear expansion coefficient of combustion chamber base material at the corresponding temperature；
And according to oxidant and fuel flow rate average value, mixing ratio r is calculated by mixing ratio computing modulem：Step Rapid 5, actual characteristic speed C is calculated by actual characteristic speed calculation module*：
Wherein, DtFor the throat diameter after temperature adjustmemt；
Step 6 utilizes chamber pressureWith mixing ratio rm, it is free that minimum gibbs is pressed by theoretical characteristic velocity computing module It can the theoretical characteristic velocity of principle calculating
Step 7 calculates engine chamber efficiency eta by engine chamber efficiency calculation modulec：
3. rocket chamber's method for analyzing efficiency according to claim 1, which is characterized in that the temperature adjustmemt Throat diameter afterwards is calculated using linear expansion coefficient
4. rocket chamber's method for analyzing efficiency according to claim 1, which is characterized in that make even to each parameter During mean value, to ensure that parameter is derived from identical engine condition, mean value calculation section is same time interval.
5. rocket chamber's method for analyzing efficiency according to claim 1, which is characterized in that engine test When parameter is averaged in the process, it is desirable that test program length can ensure that chamber pressure, oxidant and fuel flow rate, throat's temperature The parameters such as degree have enough stable sections, stablize segment length and are not less than 5s.
CN201710766220.9A 2017-08-30 2017-08-30 Rocket engine combustion chamber efficiency analysis method and system Active CN108182297B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115329695A (en) * 2022-10-11 2022-11-11 中国人民解放军63921部队 Rocket engine cooling channel outlet temperature estimation method and device

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Publication number Priority date Publication date Assignee Title
US20010003294A1 (en) * 1998-11-12 2001-06-14 Kevin E. Mahaffy Flowable solid profellant
CN103116705A (en) * 2013-02-06 2013-05-22 中国航天科技集团公司第六研究院第十一研究所 Fault simulated analysis method for afterburning cycle rocket engine
CN106134384B (en) * 2012-03-31 2014-06-18 上海空间推进研究所 The choosing method of rail control engine combustion chamber, a kind of space best features length

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Publication number Priority date Publication date Assignee Title
US20010003294A1 (en) * 1998-11-12 2001-06-14 Kevin E. Mahaffy Flowable solid profellant
CN106134384B (en) * 2012-03-31 2014-06-18 上海空间推进研究所 The choosing method of rail control engine combustion chamber, a kind of space best features length
CN103116705A (en) * 2013-02-06 2013-05-22 中国航天科技集团公司第六研究院第十一研究所 Fault simulated analysis method for afterburning cycle rocket engine

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Title
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115329695A (en) * 2022-10-11 2022-11-11 中国人民解放军63921部队 Rocket engine cooling channel outlet temperature estimation method and device

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