CN115901268A - Method for accurately acquiring total pressure loss coefficient of combustion chamber on engine - Google Patents
Method for accurately acquiring total pressure loss coefficient of combustion chamber on engine Download PDFInfo
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- CN115901268A CN115901268A CN202211393870.0A CN202211393870A CN115901268A CN 115901268 A CN115901268 A CN 115901268A CN 202211393870 A CN202211393870 A CN 202211393870A CN 115901268 A CN115901268 A CN 115901268A
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Abstract
The utility model belongs to the field of aeroengine design, for a method of accurate acquisition combustion chamber total pressure loss coefficient on engine, the mode of numerical value replacement is adopted, found with main combustion chamber diffuser export total pressure numerical value, main combustion chamber flame tube export total pressure numerical value is the same, but it is more convenient to measure, two data that the result can be accurate replace main combustion chamber diffuser export total pressure numerical value and main combustion chamber flame tube export total pressure, can directly develop the direct measurement of main combustion chamber diffuser and combustion section total pressure recovery coefficient on the complete machine, can reduce the error that numerical simulation and part test result and complete machine operating condition exist, the measuring result is more accurate, it is more practical, aeroengine combustion efficiency under the complete machine is assessed for the accuracy, and carry out performance matching design and optimization to engine complete machine each part and provide key numerical value and support.
Description
Technical Field
The application belongs to the field of design of aero-engines, and particularly relates to a method for accurately obtaining a total pressure loss coefficient of a combustion chamber on an engine.
Background
The main combustion chamber of an aircraft engine is generally composed of a diffusion section and a combustion section. When the performance of a main combustion chamber of an aircraft engine is evaluated and all parts of the whole engine of the engine are matched, designed and optimized, the total pressure recovery coefficients of a diffusion section and a combustion section of the main combustion chamber need to be accurately obtained. Because the pressure and temperature inside the main combustion chamber and at the outlet are very high and are inside the engine, the total pressure recovery coefficient of the combustion chamber can only be obtained by carrying out numerical simulation analysis and a main combustion chamber component blowing test in the prior art.
The defects of obtaining the total pressure recovery coefficient of the combustion chamber by carrying out numerical simulation analysis and a main combustion chamber component blowing test are mainly reflected as follows:
1) The numerical simulation method needs to input accurate parameters of an inlet and an outlet of a combustion chamber and boundary conditions, but the parameters of the inlet and the outlet of the combustion chamber cannot be accurately obtained by the current test conditions, particularly the temperature of the outlet of the combustion chamber is extremely high, and a sensed part cannot be arranged to measure total pressure, so that the precision of a numerical simulation result cannot be guaranteed;
2) Although the total pressure values of the inlet and the outlet of the combustion chamber can be obtained in the main combustion chamber component blowing test, the temperature environment of the combustion chamber under the whole machine cannot be simulated, and certain deviation exists between the test result and the real total pressure recovery coefficient under the whole machine.
Therefore, how to more effectively obtain the total pressure recovery coefficient of the combustion chamber is a problem to be solved.
Disclosure of Invention
The application aims to provide a method for accurately obtaining the total pressure loss coefficient of a combustion chamber on an engine so as to solve the problem that the measurement precision of the total pressure recovery coefficient of the combustion chamber in the prior art cannot be guaranteed.
The technical scheme of the application is as follows: a method of accurately obtaining a combustion chamber total pressure loss coefficient on an engine, comprising: obtaining a main combustion chamber inlet total pressure P3, a main combustion chamber two-strand airflow channel static pressure dPs32_1 with the same main combustion chamber diffusion section outlet total pressure value and a main combustion chamber flame tube internal static pressure dPs32_2 with the same main combustion chamber flame tube outlet total pressure value in the whole aircraft engine working process; the total pressure recovery coefficient of the diffusion section of the combustion chamber is determined according to the numerical values of static pressures dPs32_ dif1 of the two air flow channels of the combustion chamber and total pressure P3 of the inlet of the combustion chamber, the total pressure recovery coefficient of the combustion section of the combustion chamber is determined according to the numerical values of the static pressures dPs32_2 in the flame tube of the main combustion chamber and the static pressures dPs32_ dif1 of the two air flow channels of the main combustion chamber, and the total pressure recovery coefficient of the combustion chamber is determined according to the static pressures dPs32_2 in the flame tube of the main combustion chamber and the total pressure P3 of the inlet of the combustion chamber.
Preferably, the total pressure recovery coefficient of the diffuser section of the combustion chamber is as follows: dpp 32_ dif1= dpp 32_1/P3.
Preferably, the total pressure recovery coefficient of the combustion section of the combustion chamber is as follows: dpps 32_ dif2= dpps 32_ 2/dpps 32_1.
Preferably, the total pressure recovery coefficient of the combustion chamber is: dpps 32_ dif3= dpps 32_2/P3.
Preferably, the measurement method of the main combustion chamber two-strand airflow channel static pressure dPs32_1 and the main combustion chamber flame tube internal static pressure dPs32_2 is as follows: a pressure difference sensor is selected at a mixing hole of a flame tube, two output ends of the pressure difference sensor are respectively used for measuring static pressures dPs32_1 of two air flow channels of a main combustion chamber and static pressures dPs32_2 in the flame tube of the main combustion chamber, adjusting gaskets with different thicknesses are installed, a connecting line angle of 2 threaded holes in a cross section adapter is enabled to be parallel to the downwind direction by adjusting the cross section adapter, and after the cross section adapter is adjusted to the right position, 2 bolt holes in the pressure difference sensor are fixed on the 2 threaded holes parallel to the downwind direction through screws.
The utility model provides a method of accurate acquisition combustion chamber total pressure loss coefficient on engine, the mode of numerical value replacement is adopted, found with main combustion chamber diffuser export total pressure numerical value, main combustion chamber flame tube export total pressure numerical value is the same, but it is more convenient to measure, two data that the result can be accurate replace main combustion chamber diffuser export total pressure numerical value and main combustion chamber flame tube export total pressure, can directly develop the direct measurement of main combustion chamber diffuser and combustion section total pressure recovery numerical value on the complete machine, can reduce the error that numerical simulation and part test result and complete machine operating condition exist, the measuring result is more accurate, it is more practical, for accurately assessing aeroengine combustion efficiency under the complete machine, and carry out the performance matching design and optimize to each part of the complete machine of engine and provide key numerical value and support.
Drawings
In order to more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly described below. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
FIG. 1 is a schematic overall flow diagram of the present application;
FIG. 2 is a schematic view of circumferential distribution of the measuring points of the present application;
fig. 3 is a schematic view of a sensor mounting structure according to the present application.
1. A differential pressure sensor; 2. a section adapter; 3. and adjusting the gasket.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A method for accurately obtaining the total pressure loss coefficient of a combustion chamber on an engine comprises two parts of measuring the total static pressure parameters of a diffusion section and a combustion section of a main combustion chamber and processing and analyzing measured data in the whole working process of an aeroengine.
The method comprises the following specific steps:
s100, obtaining total static pressure measurement parameters in the whole working process of the aero-engine, wherein the total static pressure measurement parameters comprise a main combustion chamber inlet total pressure P3;
static pressure dPs32_1 of two airflow channels of the main combustion chamber; according to simulation analysis and main combustion chamber component blowing test results, the static pressure of two airflow channels of the main combustion chamber is the same as the total pressure data of an outlet of a diffusion section of the main combustion chamber;
static pressure dPs32_2 in a flame tube of the main combustion chamber; according to simulation analysis and main combustion chamber part test result of blowing, there is a certain axial position on the flame tube of main combustion chamber, and the static pressure in the flame tube of main combustion chamber obtained by measuring at this position is equal to the total pressure value of the flame tube outlet of main combustion chamber in numerical value, so that the static pressure measurement data in the flame tube of main combustion chamber can be used, and the total pressure of the flame tube outlet of main combustion chamber can be represented.
The measuring points are distributed circumferentially as shown in figure 2. The measurement scheme of the main combustion chamber two-air flow channel static pressure dPs32_1 and the main combustion chamber flame tube internal static pressure dPs32_2 is shown in figure 3. Because the above parameters are all static pressure measurement, in the measuring refitting and sensor installation processes, attention needs to be paid to ensure that an air inlet of a pressure measuring point on a tested part cannot sense the air velocity.
The method for measuring the static pressure dPs32_1 of the two airflow channels of the main combustion chamber and the static pressure dPs32_2 in the flame tube of the main combustion chamber comprises the following steps: a differential pressure sensor 1 is selected at a mixing hole on a flame tube of a main combustion chamber, two output ends of the differential pressure sensor 1 are respectively used for measuring static pressures dPs32_1 of two airflow channels of the main combustion chamber and static pressures dPs32_2 in the flame tube of the main combustion chamber, and an output end on the left side in the graph 3 is used for measuring dPs32_2. The output end on the right side is used for measuring dPs32_1, and the arrow in the figure indicates the airflow direction; installing adjusting gaskets 3 with different thicknesses to adjust the section adapter 2 to enable the connecting line angle of 2 threaded holes (totally 8 threaded holes) in the section adapter 2 to be parallel to the airflow direction, adjusting the section adapter 2 in place, and fixing 2 bolt holes on the differential pressure sensor 1 on the 2 threaded holes parallel to the airflow direction through screws.
Through finding out the two air current passageway static pressures of main combustion chamber that total pressure data is the same with main combustion chamber diffuser section export, with the main combustion chamber inner static pressure of the flame tube certain axial position that total pressure numerical value equals in main combustion chamber flame tube export, the measurement of these two kinds of data is compared in main combustion chamber diffuser section export total pressure data, the measurement of main combustion chamber flame tube export total pressure and is compared more convenient, save time, and the measuring precision can effectively be guaranteed.
Step S200, determining total pressure recovery coefficients of a diffusion section of the combustion chamber according to numerical values of static pressures dPs32_ dif1 of two airflow channels of the combustion chamber and total pressures P3 of an inlet of the combustion chamber, determining total pressure recovery coefficients of a combustion section of the combustion chamber according to numerical values of static pressures dPs32_2 in a flame tube of the main combustion chamber and static pressures dPs32_ dif1 of two airflow channels of the main combustion chamber, and determining total pressure recovery coefficients of the combustion chamber according to static pressures dPs32_2 in the flame tube of the main combustion chamber and total pressures P3 of the inlet of the combustion chamber.
The ratio of the total pressure at the outlet of the diffusion section of the main combustion chamber to the total pressure at the inlet of the diffusion section is the total pressure recovery coefficient of the diffusion section of the combustion chamber, the numerical value is equal to the ratio of the static pressures dPs32_ dif1 of the two air flow channels of the main combustion chamber to the total pressure P3 at the inlet of the combustion chamber, and the calculation is carried out according to the formula 1:
dPs32_dif1= dPs32_1/P3…………………………（1）
the ratio of the total pressure at the outlet of the flame tube at the combustion section of the main combustion chamber to the total pressure at the outlet of the flame tube (total pressure at the outlet of the diffuser) is the total pressure recovery coefficient of the combustion section of the combustion chamber, and is equal to the ratio of the static pressure dPs32_2 in the flame tube of the main combustion chamber to the static pressure dPs32_ dif1 in the two air flow channels of the main combustion chamber, and the calculation is carried out according to the formula 2:
dPs32_dif2= dPs32_2/dPs32_1……………………（2）
the ratio of the total pressure at the outlet of the flame tube of the combustion section of the main combustion chamber to the total pressure at the inlet of the diffuser section is the total pressure recovery coefficient of the whole combustion chamber, the numerical value is equal to the ratio of the static pressure dPs32_2 in the flame tube of the main combustion chamber to the total pressure P3 at the inlet of the combustion chamber, and the calculation is carried out according to the formula 3:
dPs32_dif3= dPs32_2/P3………………………（3）
the method adopts a numerical value replacement mode, the total pressure numerical value of the outlet of the main combustion chamber diffusion section is found, the total pressure numerical value of the outlet of the flame tube of the main combustion chamber is the same, but the measurement is more convenient, the total pressure numerical value of the outlet of the main combustion chamber diffusion section and the total pressure of the outlet of the flame tube of the main combustion chamber are replaced by two data with accurate results, the direct measurement of the total pressure numerical values of the main combustion chamber diffusion section and the combustion section on the complete machine can be directly carried out, errors of numerical simulation and part test results and complete machine working conditions can be reduced, the measurement result is more accurate and more practical, the combustion efficiency of the aero-engine under the complete machine is accurately evaluated, and key numerical value support is provided for carrying out performance matching design and optimization on all parts of the complete machine of the engine.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A method for accurately obtaining a combustion chamber total pressure loss coefficient on an engine, comprising:
obtaining a main combustion chamber inlet total pressure P3, a main combustion chamber two-strand airflow channel static pressure dPs32_1 with the same main combustion chamber diffusion section outlet total pressure value and a main combustion chamber flame tube internal static pressure dPs32_2 with the same main combustion chamber flame tube outlet total pressure value in the whole working process of the aero-engine;
the total pressure recovery coefficient of the diffusion section of the combustion chamber is determined according to the numerical values of static pressures dPs32_ dif1 of the two air flow channels of the combustion chamber and total pressure P3 of the inlet of the combustion chamber, the total pressure recovery coefficient of the combustion section of the combustion chamber is determined according to the numerical values of the static pressures dPs32_2 in the flame tube of the main combustion chamber and the static pressures dPs32_ dif1 of the two air flow channels of the main combustion chamber, and the total pressure recovery coefficient of the combustion chamber is determined according to the static pressures dPs32_2 in the flame tube of the main combustion chamber and the total pressure P3 of the inlet of the combustion chamber.
2. The method for accurately obtaining the total pressure loss coefficient of the combustion chamber on the engine as claimed in claim 1, wherein the total pressure loss coefficient of the diffusion section of the combustion chamber is as follows: dpps 32_ dif1= dpps 32_1/P3.
3. The method for accurately obtaining a combustor total pressure loss coefficient on an engine as set forth in claim 1, wherein the combustor combustion section total pressure recovery coefficient is: dpps 32_ dif2= dpps 32_ 2/dpps 32_1.
4. A method of accurately deriving a combustor total pressure loss coefficient on an engine as defined in claim 1 wherein said combustor total pressure loss coefficient is: dpps 32_ dif3= dpps 32_2/P3.
5. The method for accurately obtaining the total pressure loss coefficient of the combustion chamber on the engine as claimed in claim 1, wherein the measuring method of the main combustion chamber two-stream channel static pressure dPs32_1 and the main combustion chamber flame tube static pressure dPs32_2 is as follows: the method is characterized in that a differential pressure sensor (1) is selected at a mixing hole of a flame tube, two output ends of the differential pressure sensor (1) are respectively used for measuring static pressure dPs32_1 of two air flow channels of a main combustion chamber and static pressure dPs32_2 in the flame tube of the main combustion chamber, adjusting gaskets (3) with different thicknesses are installed, a connecting line angle of 2 threaded holes in a cross section adapter (2) is enabled to be parallel to the airflow direction by adjusting the cross section adapter (2), and after the cross section adapter (2) is adjusted in place, 2 bolt holes in the differential pressure sensor (1) are fixed on 2 threaded holes parallel to the airflow direction through screws.
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Cited By (1)
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| CN116562193A (en) * | 2023-07-10 | 2023-08-08 | 中国人民解放军空军工程大学 | Combustion efficiency analysis method and system for rotary detonation engine |
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