CN111256967B - Method for measuring effective throat area of supersonic turbine nozzle and server - Google Patents
Method for measuring effective throat area of supersonic turbine nozzle and server Download PDFInfo
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Abstract
The invention provides a method for measuring the effective throat area of a supersonic turbine nozzle and a server. The measuring method comprises the following steps: taking the first fluid as a medium, and acquiring a first reference throat area of the first turbine nozzle in a cavitation state; taking the second fluid as a medium, acquiring a first effective throat area of the first turbine nozzle in a hot test state, and calculating to obtain a ratio a of a first reference throat area to the first effective throat area; in the later period, the first fluid is used as a medium, and a second reference throat area of the second turbine nozzle in a cavitation state is obtained; and directly calculating to obtain a second effective throat area of the second turbine nozzle in a hot test state with a second fluid according to the ratio a and the second reference throat area. The measuring method of the invention obtains the early-stage data through a simple liquid flow test system, and then obtains the effective throat area of the turbine nozzle through corresponding formula calculation, thus ensuring simple, fast, safe and low cost measuring process.
Description
Technical Field
The invention relates to the technical field of rocket engines, in particular to a method for measuring the effective throat area of a supersonic turbine nozzle and a server.
Background
The supersonic turbine nozzle in the turbine air inlet housing is a key component of a turbopump of a liquid rocket engine, and the main function of the supersonic turbine nozzle is to accelerate high-temperature and high-pressure gas from a generator to generate supersonic airflow. Theoretically, the throat area of the turbine nozzle is in direct proportion to the flow, the size of the throat area directly influences the flow of the working medium, the output power of the turbine is further influenced, and the adjustment of an engine system is very important, so that the effective throat area of the turbine nozzle needs to be accurate as much as possible when each engine is in a hot test.
At present, in order to measure the effective throat area of a supersonic turbine nozzle, a widely adopted method is a blowing test. For the supersonic nozzle, the air blowing test nozzle is high in air flow speed and large in noise, damage to auditory systems of testers is easily caused, a high-pressure air source is needed in an air flow test, the single test period is long, the test bench is high in cost, and the test device and an additional system are complex.
Disclosure of Invention
In view of the above technical problems in the related art, the present invention provides a method and a server for measuring an effective throat area of a supersonic turbine nozzle. The measuring method has the advantages of low noise, short test period, low measurement difficulty and test cost saving.
One aspect of the present invention provides a method of measuring an effective throat area of a supersonic turbine nozzle. The measuring method comprises the following steps:
taking the first fluid as a medium, and acquiring a first reference throat area of the first turbine nozzle in a cavitation state;
taking a second fluid as a medium, acquiring a first effective throat area of the first turbine nozzle in a hot test state, and calculating to obtain a ratio a of the first reference throat area to the first effective throat area;
taking the first fluid as a medium, and acquiring a second reference throat area of the second turbine nozzle in a cavitation state;
acquiring a second effective throat area of the second turbine nozzle in a hot test state with the second fluid according to the ratio a and the second reference throat area; wherein the first turbine nozzle and the second turbine nozzle are the same specification nozzles.
Further, the method for obtaining the first reference throat area of the first turbine nozzle in the cavitation state by using the first fluid as a medium comprises the following steps:
wherein C is the flow coefficient, A1 is the throat area, and the unit is mm2(ii) a C × a1 is a first reference throat area; qm1 is the mass flow rate of the first fluid in kg/s; pi1 is the total inlet pressure in MPa; ps1 is the saturated vapor pressure in the cavitation state, in MPa; ρ 1 is the density of the first fluid in the cavitation state, in kg/m3。
Further, the method for obtaining the first effective throat area of the first turbine nozzle in the hot test state by using the second fluid as a medium and calculating the ratio a of the first reference throat area to the first effective throat area includes:
wherein
Wherein Qmf is the mass flow rate of the second fluid in kg/s; r is the second fluid index calculated by the mixing ratio; pi is total inlet pressure in MPa; r is the second fluid gas constant calculated by the mixing ratio; ti is the total inlet temperature and the unit is K; cf is a flow coefficient; a1 is throat area in mm2(ii) a Cf a1 is the first effective throat area.
Calculating to obtain the first effective throat area Cf A, and then passing through a formula:
a is calculated as (C a1)/(Cf a 1).
Further, a method for obtaining a second reference throat area of the second turbine nozzle in a cavitation state by taking the first fluid as a medium is as follows;
wherein C is the flow coefficient, A2 is the throat area, and the unit is mm2(ii) a C × a2 is a second reference throat area; qm2 is the mass flow rate of the first fluid in kg/s; pi2 is the total inlet pressure in MPa; ps2 is the saturated vapor pressure in the cavitation state, in MPa; ρ 2 is the density of the first fluid in the cavitation state, and the unit is kg/m3。
Further, the method for obtaining the second effective throat area of the second turbine nozzle in the hot-test state with the second fluid according to the ratio a and the second reference throat area comprises the following steps: obtaining the second effective throat area from a ratio of the second reference throat area to an a value of the second turbine nozzle by:
wherein Cf A2 is the second effective throat area and C A2 is the second reference throat area.
Further, before obtaining the first reference throat area of the first turbine nozzle in the cavitation state by using the first fluid as a medium, the method further includes: and gradually changing the total inlet pressure by using the first fluid as a medium, and determining that the cavitation state exists when the first reference throat area C x A1 values obtained under different total inlet pressure values are close and within an allowable error.
Further, before obtaining a second reference throat area of the second turbine nozzle in the cavitation state by using the first fluid as a medium, the method further includes: gradually changing the inlet total pressure using the first fluid as a medium, and determining that a cavitation condition has been reached when said second reference throat area values obtained at different inlet total pressure values are similar and within an allowable error.
Further, the obtaining, by calculation, a ratio a of the first reference throat area to the first effective throat area specifically includes: respectively acquiring reference throat areas and effective throat areas of a plurality of turbine nozzles with the same specification, and calculating the ratio of the reference throat area to the effective throat area of each turbine nozzle; when the ratio values are close and within the allowable error range, taking the average value of the ratios as the ratio a.
In one embodiment, the measuring device for performing the liquid flow test by using the first fluid as a medium comprises: the liquid storage device is used for storing the first fluid, the valve is used for controlling the flow of liquid water, the flow measuring device is used for measuring the flow of the fluid, the pressure measuring device is used for measuring the pressure of the fluid, and the temperature measuring device is used for measuring the temperature of the fluid. And adjusting the water flow entering the turbine nozzle by adjusting the valve, stopping adjusting the valve when the turbine nozzle reaches a critical state (namely a cavitation state), and calculating to obtain a value of the first reference throat area according to parameters of the flow measuring device, the pressure measuring device and the temperature measuring device, the searched saturated vapor pressure value at the inlet temperature and the searched density value of the liquid water.
In one embodiment, the inlet total pressure is measured by a pressure sensor disposed at the inlet of the first fluid during the test with the first fluid as the medium.
In one embodiment, the total inlet temperature is measured by a temperature sensor arranged at the inlet of the first fluid during the test with the first fluid as the medium.
Another aspect of the present invention provides a server, including a memory and a processor, wherein the memory stores an executable program, and the processor is configured to call the executable program to perform the above-mentioned measurement method.
According to the method for measuring the effective throat area of the supersonic turbine nozzle, the ratio a of the reference throat area to the effective throat area is obtained through early-stage test calculation, and then the effective throat area of the turbine nozzle to be measured in the later stage can be obtained through calculation in combination with the ratio a after the reference throat area is measured, so that the effective throat area of the supersonic turbine nozzle can be measured quickly and accurately.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a flow chart of a method of measuring an effective throat area of a supersonic nozzle in accordance with an embodiment of the present invention.
FIG. 2 is a block diagram of a measurement device for performing a flow test with a first medium according to an embodiment of the present invention.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
The invention provides a method for measuring the effective throat area of a supersonic turbine nozzle. The measuring method is mainly used for measuring the effective throat area of the supersonic speed turbine nozzle of the rocket engine. Referring to fig. 1, the method for measuring the effective throat area of the supersonic turbine nozzle of the rocket engine comprises the following steps:
s10, taking the first fluid as a medium, obtaining a first reference throat area of the first turbine nozzle in a cavitation state.
S20, taking the second fluid as a medium, obtaining a first effective throat area of the first turbine nozzle in a hot test state, and obtaining a ratio a of a first reference throat area to the first effective throat area through calculation.
S30, taking the first fluid as a medium, acquiring a second reference throat area of the second turbine nozzle in a cavitation state.
S40, acquiring a second effective throat area of the second turbine nozzle in a hot test state with a second fluid according to the ratio a and a second reference throat area; wherein the first turbine nozzle and the second turbine nozzle are nozzles of the same specification.
In the embodiment of the invention, in the early stage, a first fluid is used as a medium to perform a fluid flow test, a first reference throat area of a first turbine nozzle in a cavitation state is obtained, then, the same turbine nozzle is subjected to a hot test run test by using a second fluid as a medium to obtain a first effective throat area, and a constant a is obtained by calculating the ratio of the first reference throat area to the first effective throat area. And in the later stage, after the second turbine nozzle performs a liquid flow test by taking the first fluid as a medium and acquires a second reference throat area of the second turbine nozzle in a cavitation state, the second effective throat area of the second turbine nozzle can be directly calculated according to the ratio constant a.
Preferably, the first fluid may be liquid water and the second fluid may be gas. The liquid water has low cost and low danger, and can be used for carrying out liquid flow tests more safely and reliably by utilizing the characteristics of non-compressibility, non-flammability and easiness in acquisition.
Further, the method for obtaining the first reference throat area of the first turbine nozzle in the cavitation state by using liquid water as a medium comprises the following steps:
wherein C is the flow coefficient, A1 is the throat area, and the unit is mm2(ii) a C × a1 is a first reference throat area; qm1 is the mass flow rate of the first fluid in kg/s; pi1 is the total inlet pressure in MPa; ps1 is the saturated vapor pressure in the cavitation state, in MPa; ρ 1 is the density of the first fluid in the cavitation state, in kg/m3。
In the embodiment of the invention, under the liquid flow test cavitation state with liquid water as a medium, test data such as mass flow Qm1, inlet total pressure Pi1, saturated vapor pressure Ps1, liquid water density rho 1 and the like are correspondingly brought into a formula:
Referring to fig. 2, in particular, the measuring device for liquid flow test with liquid water as medium includes: the device comprises a liquid storage device 1, a pumping pressure device 2, a valve 3, a flow measuring device 4, a pressure measuring device 5, a temperature measuring device 6 and a turbine nozzle (a first turbine nozzle) 7 which are sequentially connected through pipelines. The liquid storage device 1 is used for storing liquid water, the valve 3 is used for controlling the flow of the liquid water, the flow measuring device 4 is used for measuring the flow of fluid, the pressure measuring device 5 is used for measuring the pressure of the fluid, and the temperature measuring device 6 is used for measuring the temperature of the fluid. The water flow into the turbine nozzle 7 is adjusted by adjusting the opening of the valve 3, and when the turbine nozzle 7 reaches a critical state (i.e., a cavitation state), the adjustment of the valve 3 is stopped. And calculating to obtain a value of the first reference throat area according to the parameters of the flow measuring device 4, the pressure measuring device 5 and the temperature measuring device 6, the searched saturated vapor pressure value at the inlet temperature and the density value of the liquid water.
With continued reference to fig. 1, further, the method for obtaining the first effective throat area of the first turbine nozzle in the hot-test condition with the combustion gas as the medium is as follows:
wherein
Wherein Qmf is the mass flow rate of the second fluid in kg/s; r is the second fluid index calculated by the mixing ratio; pi is total inlet pressure in MPa; r is the second fluid gas constant calculated by the mixing ratio; ti is the total inlet temperature and the unit is K; cf is a flow coefficient; a1 is throat area in mm2(ii) a And Cf a1 is the first effective throat area. After the first effective throat area Cf × a1 is obtained by calculation, a ratio a of the first reference throat area to the first effective throat area obtained by calculation is as follows:a＝(C*A1)/(Cf*A1)。
in the embodiment of the invention, the first turbine nozzle is subjected to a hot test run test, and test data such as mass flow Qmf, gas index R, inlet total pressure Pi, gas constant R and inlet total temperature Ti are substituted into a corresponding formula:
a value for the first effective throat area Cf a1 is thus calculated. The value of the constant a can be obtained by calculating a ═ (C × a1)/(Cf × a 1).
Further, a method for acquiring a second reference throat area of the second turbine nozzle in a cavitation state by using liquid water as a medium comprises the following steps of;
wherein C is the flow coefficient, A2 is the throat area, and the unit is mm2(ii) a C × a2 is a second reference throat area; qm2 is the mass flow rate of the first fluid in kg/s; pi2 is the total inlet pressure in MPa; ps2 is the saturated vapor pressure in the cavitation state, in MPa; ρ 2 is the density of the first fluid in the cavitation state, and the unit is kg/m3。
In the embodiment of the invention, the test data such as the mass flow Qm2, the inlet total pressure Pi2, the saturated vapor pressure Ps2 and the liquid water density rho 2 obtained in the liquid flow test cavitation state with liquid water as a medium are correspondingly brought into a formula:
a second reference throat area C x a2 value is calculated. Referring to fig. 2, specifically, by adjusting the valve 3 and thus adjusting the flow rate of water into the turbine nozzle (second turbine nozzle) 7, the valve 3 is stopped when the turbine nozzle 7 reaches a critical state (i.e., a cavitation state). And calculating to obtain a second reference throat area value according to the parameters of the flow measuring device 4, the pressure measuring device 5 and the temperature measuring device 6, the searched saturated vapor pressure value at the inlet temperature and the density value of the liquid water. A second effective throat area Cf A2 is then obtained based on a ratio of a second reference throat area C A2 of the second turbine nozzle to the value a.
Furthermore, the effective throat area directly influences the working medium flow during the thermal test, further influences the output power of the turbine, and is very important for adjusting an engine system, so that the effective throat area of the turbine nozzle during the thermal test of each engine needs to be as accurate as possible. According to the embodiment of the invention, after the value of the second effective throat area Cf A2 is obtained through calculation, the mass flow of the fuel gas of the second turbine nozzle during the hot test can be reversely pushed through the value of the second effective throat area Cf A2, so that the mass flow of the fuel gas can be controlled when the hot test is required to be carried out on the second turbine nozzle due to other reasons in the later period, and the accuracy of the system flow regulation is improved.
Referring to fig. 2, in an embodiment, before obtaining the first reference throat area of the first turbine nozzle in the cavitation state by using liquid water as a medium, the method further includes the following steps: by gradually changing the total pressure at the inlet of the first turbine nozzle using liquid water stored in the liquid storage device 1 as a medium, it can be determined that the turbine nozzle has reached a cavitation state when the first reference throat area C x a1 values obtained at different inlet total pressure values are close and within an allowable error.
As above, before obtaining the second reference throat area of the second turbine nozzle in the cavitation state by using liquid water as a medium, the method further includes the following steps: gradually changing the total pressure at the inlet of the second turbine nozzle using liquid water as a medium, and determining that the cavitation state has been reached when the second reference throat area values obtained at different inlet total pressure values are close and within an allowable error.
Specifically, for example, in a liquid flow test using liquid water as a medium, after the pumping device 2 is opened, the opening degree of the valve 3 is adjusted to adjust the total fluid pressure at the inlet. For example, when the pressure measuring device 5 detects pressure values of 0.6 ± 0.01MPa, 0.7 ± 0.01MPa, and 0.8 ± 0.01MPa, parameters of the flow measuring device 4, the pressure measuring device 5, and the temperature measuring device 6 are respectively recorded, a value of the reference throat area is calculated according to a formula, and when the values of the reference throat area are close and within an allowable error at three pressure values, it can be determined that the turbine nozzle is in a cavitation state at the above three pressure values.
Further, the obtaining, by calculation, a ratio a of the first reference throat area to the first effective throat area specifically includes: respectively acquiring reference throat areas and effective throat areas of a plurality of turbine nozzles with the same specification, and calculating the ratio of the reference throat area to the effective throat area of each turbine nozzle; when the values of the ratios are close and within the allowable error range, the average value of the ratios can be taken as the ratio a. According to the embodiment of the invention, the liquid flow test and the hot test run test are carried out one by adopting a plurality of turbine nozzles with the same specification, a plurality of ratio constants are obtained through calculation, after a plurality of groups of data are accumulated, when the numerical values of the plurality of ratio constants are close and within an allowable error range, the average value of the plurality of ratios is used as the ratio constant a, and thus the measurement accuracy of the turbine nozzles is improved.
Referring to fig. 2, in one embodiment, during the liquid flow test with liquid water as the medium, the total inlet pressure is measured by a pressure measuring device 5 disposed at the inlet of the liquid water. For example, the total inlet pressure is measured by a pressure sensor disposed at the liquid water inlet.
In one embodiment, the total inlet temperature is measured by a temperature measuring device 6 arranged at the inlet of the liquid water during the liquid flow test with the liquid water as the medium. For example, the total inlet temperature is measured by a temperature sensor disposed at the liquid water inlet.
In one embodiment, the mass flow rate of liquid water during the liquid flow test with liquid water as the medium is measured by a flow measuring device 4 arranged at the liquid water inlet. For example, the total inlet temperature is measured by a flow sensor disposed at the liquid water inlet.
The method for measuring the effective throat area of the supersonic turbine nozzle has the advantages of simple and direct measuring process, short period and low cost, improves the reliability, the accuracy and the safety, and can quickly and accurately finish the measurement of the effective throat area of the turbine nozzle, thereby ensuring the output power of a turbine product and improving the adjusting performance of an engine system.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
Another aspect of the present invention provides a server, including a memory and a processor, wherein the memory stores an executable program, and the processor is configured to call the executable program to perform the above-mentioned measurement method.
The measurement methods of the embodiments of the present invention described above may be implemented in various hardware, software code, or a combination of both. The server of the present invention may be involved in a variety of functions performed by a computer processor, digital signal processor, microprocessor, or Field Programmable Gate Array (FPGA). The processor described above may be configured according to the present invention to perform certain tasks by executing machine-readable software code or firmware code that defines certain methods disclosed herein. Software code or firmware code may be developed in different programming languages and in different formats or forms. Software code may also be compiled for different target platforms. However, the different code styles, types, and languages of software code and other types of configuration code that perform tasks in accordance with the present invention do not depart from the spirit and scope of the present invention.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. A method of measuring an effective throat area of a supersonic turbine nozzle, comprising the steps of:
taking the first fluid as a medium, and acquiring a first reference throat area of the first turbine nozzle in a cavitation state; the method specifically comprises the following steps:
taking a second fluid as a medium, acquiring a first effective throat area of the first turbine nozzle in a hot test state, and calculating to obtain a ratio a of the first reference throat area to the first effective throat area; the method specifically comprises the following steps:
wherein
Secondly, by the formula: a is calculated as (C a1)/(Cf a 1);
taking the first fluid as a medium, and acquiring a second reference throat area of the second turbine nozzle in a cavitation state; the method specifically comprises the following steps:
acquiring a second effective throat area of the second turbine nozzle in a hot test state with the second fluid according to the ratio a and the second reference throat area; wherein the first turbine nozzle and the second turbine nozzle are the same specification nozzles;
in the above formula, where C is the flow coefficient, a1 is the throat area of the first turbine nozzle, a2 is the throat area of the second turbine nozzle, C × a1 is the first reference throat area, C × a2 is the second reference throat area; qm1, Qm2 are the mass flow rate of the first fluid; pi1 and Pi2 are inlet total pressures; ps1 and Ps2 are saturated vapor pressures in the cavitation state; ρ 1 and ρ 2 are densities of the first fluid in a cavitation state; qmf is the mass flow rate of the second fluid; r is the second fluid index calculated by the mixing ratio; pi is inlet total pressure; r is the second fluid gas constant calculated by the mixing ratio; ti is the inlet total temperature; cf is a flow coefficient; a1 is the throat area and Cf a1 is the first effective throat area.
2. A method of measuring an effective throat area of a supersonic turbine nozzle as defined in claim 1, wherein said obtaining a second effective throat area of said second turbine nozzle under hot-test conditions with said second fluid based on said ratio a and said second reference throat area comprises:
obtaining the second effective throat area from a ratio of the second reference throat area to an a value of the second turbine nozzle, specifically:
wherein Cf A2 is the second effective throat area and C A2 is the second reference throat area.
3. The method of claim 1, wherein said obtaining a first reference throat area of the first turbine nozzle in a cavitation state with the first fluid as a medium further comprises:
and gradually changing the total inlet pressure by using the first fluid as a medium, and determining that the cavitation state exists when the first reference throat area C x A1 values obtained under different total inlet pressure values are close and within an allowable error.
4. A method of measuring an effective throat area of a supersonic turbine nozzle as defined in claim 1, wherein said deriving a second reference throat area of a second turbine nozzle in a cavitation mode using said first fluid as a medium further comprises:
gradually changing the inlet total pressure using the first fluid as a medium, and determining that a cavitation condition has been reached when said second reference throat area values obtained at different inlet total pressure values are similar and within an allowable error.
5. A method of measuring an effective throat area of a supersonic turbine nozzle as defined in any one of claims 1 to 4, wherein said obtaining a ratio a of said first reference throat area to said first effective throat area by calculation comprises:
respectively acquiring reference throat areas and effective throat areas of a plurality of turbine nozzles with the same specification, and calculating the ratio of the reference throat area to the effective throat area of each turbine nozzle; when the ratio values are close and within the allowable error range, taking the average value of the ratios as the ratio a.
6. A method of measuring an effective throat area of a supersonic turbine nozzle as defined in claim 5, wherein said inlet total pressure is measured during a test with said first fluid as a medium by a pressure sensor disposed at an inlet of said first fluid.
7. A method of measuring an effective throat area of a supersonic turbine nozzle as defined in claim 6, wherein said total inlet temperature is measured during a test with said first fluid as a medium by a temperature sensor disposed at an inlet of said first fluid.
8. A server comprising a memory storing an executable program and a processor for invoking the executable program to perform a measurement method as claimed in any one of claims 1-7.
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| CN101576026A (en) * | 2007-12-06 | 2009-11-11 | 斯奈克玛公司 | Rocket engine nozzle system |
| CN103573760A (en) * | 2013-10-15 | 2014-02-12 | 西安交通大学 | Device for realizing incompressible fluid critical flow by applying mechanical choking principle |
| CN109139296A (en) * | 2018-09-11 | 2019-01-04 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| CN209745566U (en) * | 2019-05-20 | 2019-12-06 | 九州云箭(北京)空间科技有限公司 | Test device for thrust adjusting system of rocket engine |
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| US7251925B2 (en) * | 2004-10-14 | 2007-08-07 | Hamilton Sundstrand Corporation | Pressure-based fuel metering unit |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101576026A (en) * | 2007-12-06 | 2009-11-11 | 斯奈克玛公司 | Rocket engine nozzle system |
| CN103573760A (en) * | 2013-10-15 | 2014-02-12 | 西安交通大学 | Device for realizing incompressible fluid critical flow by applying mechanical choking principle |
| CN109139296A (en) * | 2018-09-11 | 2019-01-04 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| CN209745566U (en) * | 2019-05-20 | 2019-12-06 | 九州云箭(北京)空间科技有限公司 | Test device for thrust adjusting system of rocket engine |
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