CN115292669A - Calculation method for overall performance of core engine of aircraft engine - Google Patents
Calculation method for overall performance of core engine of aircraft engine Download PDFInfo
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- CN115292669A CN115292669A CN202210902975.8A CN202210902975A CN115292669A CN 115292669 A CN115292669 A CN 115292669A CN 202210902975 A CN202210902975 A CN 202210902975A CN 115292669 A CN115292669 A CN 115292669A
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- G06F17/10—Complex mathematical operations
- G06F17/18—Complex mathematical operations for evaluating statistical data, e.g. average values, frequency distributions, probability functions, regression analysis
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- G06F17/11—Complex mathematical operations for solving equations, e.g. nonlinear equations, general mathematical optimization problems
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Abstract
The application belongs to the technical field of overall performance evaluation of an aircraft engine core, and particularly relates to an overall performance calculation method of the aircraft engine core, which comprises the following steps: identifying a typical leak location for the core machine; calculating the air leakage of a typical air leakage position of the core machine; analyzing the influence of the air leakage of the typical position on the performance of the core machine component, and further calculating the performance of the core machine component; correcting a core machine flow balance equation and a work balance equation based on the typical position air leakage; and calculating the overall performance of the core machine according to the performance of the core machine components, the flow balance equation of the core machine and the work balance equation.
Description
Technical Field
The application belongs to the technical field of overall performance evaluation of an aircraft engine core, and particularly relates to a method for calculating overall performance of the aircraft engine core.
Background
The core engine is a core component of the aero-engine, mainly comprises a gas compressor, a combustion chamber connected behind the gas compressor and a turbine connected behind the combustion chamber, accurately evaluates the overall performance of the core engine, and can provide support for the design and improvement of the aero-engine.
Currently, the following two methods are mainly adopted for evaluating the overall performance of the core machine:
1) Based on the performance evaluation of the test, the corresponding test needs to be designed and developed, which is time-consuming, labor-consuming and low in efficiency;
2) The performance evaluation based on calculation is based on calculation, so that a large amount of manpower and material resources can be saved, the efficiency is high, but the influence of the air leakage performance of the core engine is not considered during calculation, so that the evaluation result of the overall performance of the core engine is easy to generate larger deviation in practice, and the design and the improvement of the aero-engine are difficult to support.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method for calculating the overall performance of an aircraft engine core to overcome or mitigate the technical disadvantages of at least one aspect of the known existence.
The technical scheme of the application is as follows:
an aircraft engine core machine overall performance calculation method comprises the following steps:
identifying a typical leak location for the core machine;
calculating the air leakage amount of a typical air leakage position of the core machine;
analyzing the influence of the air leakage of the typical position on the performance of the core machine component, and further calculating the performance of the core machine component;
correcting a core machine flow balance equation and a work balance equation based on the air leakage of the typical position;
and calculating to obtain the overall performance of the core machine according to the performance of the core machine components, the flow balance equation of the core machine and the work balance equation.
According to at least one embodiment of the application, in the method for calculating the overall performance of the aircraft engine core, the typical leakage position of the core includes a connection part between a compressor casing and a combustion chamber casing, and a connection part between a combustion chamber flame tube and a turbine guide vane.
According to at least one embodiment of the application, in the above method for calculating the overall performance of the core of the aircraft engine, the air leakage amount at the typical air leakage position of the core is obtained by a sealing test, and specifically:
plugging a gas leakage position on the core machine except the typical gas leakage position of the gas leakage amount to be obtained;
measuring the air inlet flow and the air outlet flow of the core machine;
and subtracting the difference value of the air inlet flow and the air outlet flow of the core machine to obtain the air leakage of the typical air leakage position of the air leakage to be obtained.
According to at least one embodiment of the application, in the above method for calculating the overall performance of the core of the aircraft engine, the calculation of the air leakage amount at the typical air leakage position of the core is performed by deformation calculation, and specifically:
calculating a cold state gap at a typical air leakage position of the air leakage to be obtained;
calculating a temperature field at a typical air leakage position of the air leakage to be obtained;
calculating a thermal state gap at the typical air leakage position of the air leakage to be obtained according to the cold state gap and the temperature field at the typical air leakage position of the air leakage to be obtained;
and calculating the air leakage at the typical air leakage position of the air leakage to be obtained according to the thermal state gap at the typical air leakage position of the air leakage to be obtained and the pneumatic boundary conditions of the thermal state gap.
According to at least one embodiment of the application, in the above method for calculating the overall performance of the aircraft engine core, the calculating the performance of the core component includes:
considering the air leakage of the connecting part between the flame tube and the turbine guide vane of the combustion chamber, and calculating the total pressure recovery coefficient of the combustion chamber;
considering the air leakage of the connection part between the flame tube and the turbine guide vane of the combustion chamber, and calculating the radial and circumferential unevenness of the temperature field at the outlet of the combustion chamber;
and (4) calculating the efficiency of the turbine by considering the air leakage of the connecting part between the combustor flame tube and the turbine guide vane.
According to at least one embodiment of the application, in the above method for calculating the overall performance of the core engine of the aircraft engine, the correcting the core engine flow balance equation based on the typical position air leakage includes:
w 25 -w intermediate (II) -w Rotor -w Air leakage +w f ＝w 41 ；
Wherein the content of the first and second substances,
w 25 the air flow at the inlet of the compressor;
w intermediate (II) Introducing gas flow for the middle stage of the gas compressor;
w rotor An airflow for turbine rotor blades;
w air leakage The air leakage amount is the typical air leakage position of the core machine;
w f the fuel flow of the core engine;
w 41 is the amount of airflow at the inlet of the turbine rotor.
According to at least one embodiment of the application, in the method for calculating the overall performance of the aircraft engine core engine,
wherein the content of the first and second substances,
k is a gas physical property constant at the inlet of the compressor;
A 25 the area of the inlet of the compressor;
P 25 the total pressure at the inlet of the compressor;
q 25 the mass flow of the air flow at the inlet is compressed air;
T 25 the total temperature at the inlet of the compressor.
According to at least one embodiment of the application, in the method for calculating the overall performance of the aircraft engine core engine,
wherein the content of the first and second substances,
K g is the gas physical property constant at the inlet of the turbine rotor;
A 41 is the area at the inlet of the turbine rotor;
P 41 total pressure at the inlet of the turbine rotor;
q 41 mass flow of the gas flow at the inlet of the turbine rotor;
T 41 is the total temperature at the inlet of the turbine rotor.
According to at least one embodiment of the application, in the above method for calculating the overall performance of the core engine of the aircraft engine, the correcting the core machine work balance equation based on the typical position air leakage includes:
wherein the content of the first and second substances,
T 41 the total temperature at the inlet of the turbine rotor;
T 25 the total temperature at the inlet of the compressor;
π c the expansion ratio of the compressor is;
k is a gas physical property constant at the inlet of the compressor;
η c efficiency of the compressor;
C p the specific constant pressure heat capacity of air;
C pg the specific constant pressure heat capacity of the fuel gas;
π T is the turbo-expansion ratio;
K g is the gas physical property constant at the inlet of the turbine rotor;
η T to turbine efficiency;
η machinery Mechanical efficiency;
w intermediate of Bleed air flow for the middle stage of the compressor;
w rotor Airflow for turbine rotor blades;
w air leakage The air leakage amount is the typical air leakage position of the core machine;
w f is the core engine fuel flow.
Drawings
FIG. 1 is a schematic diagram of a method for calculating overall performance of an aircraft engine core engine provided by an embodiment of the application.
For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the description of the application should not be construed as an absolute limitation of quantity, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of any other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
An aircraft engine core machine overall performance calculation method comprises the following steps:
identifying a typical leak location of the core machine;
calculating the air leakage of a typical air leakage position of the core machine;
analyzing the influence of the air leakage of the typical position on the performance of the core machine component, and further calculating the performance of the core machine component;
correcting a core machine flow balance equation and a work balance equation based on the typical position air leakage;
and calculating the overall performance of the core machine according to the performance of the core machine components, the flow balance equation of the core machine and the work balance equation.
For the method for calculating the overall performance of the core engine of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the method is designed to calculate the air leakage of the typical air leakage position of the core engine on the basis of identifying the typical air leakage position of the core engine, analyze the air leakage of the typical position, influence the core engine component performance, calculate the core engine component performance by considering the air leakage of the typical position, correct the core engine flow balance equation and the function balance equation on the basis of the air leakage of the typical position, and further calculate the overall performance of the core engine by using the core engine component performance, the core engine flow balance equation and the function balance equation, so that a large amount of manpower and material resources can be saved, the efficiency is high, and in addition, the evaluation result of the overall performance of the core engine has high reliability, and can support the design and improvement of the aircraft engine.
In some alternative embodiments, in the method for calculating the overall performance of the aircraft engine core, the typical leakage position of the core includes a connection portion between a compressor casing and a combustor casing, and a connection portion between a combustor liner and a turbine guide vane.
In some optional embodiments, in the above method for calculating the overall performance of the core of the aircraft engine, the calculating of the air leakage amount at the typical air leakage position of the core is performed by a sealing test, and specifically includes:
plugging a gas leakage position on the core machine except the typical gas leakage position of the gas leakage amount to be obtained;
measuring the air inlet flow and the air outlet flow of the core machine;
and (4) taking the difference value of the air inlet flow and the air outlet flow of the core machine as the air leakage of the typical air leakage position of the air leakage to be obtained.
In some optional embodiments, in the above method for calculating the overall performance of the core of the aircraft engine, the calculating of the air leakage amount at the typical air leakage position of the core is performed by deformation calculation, specifically:
calculating a cold state gap at a typical air leakage position of the air leakage to be obtained;
calculating a temperature field at a typical air leakage position of the air leakage to be obtained;
calculating a thermal state gap at the typical air leakage position of the air leakage to be obtained according to the cold state gap and the temperature field at the typical air leakage position of the air leakage to be obtained;
and calculating the air leakage at the typical air leakage position of the air leakage to be calculated according to the thermal state gap at the typical air leakage position of the air leakage to be calculated and the pneumatic boundary condition of the thermal state gap.
In some optional embodiments, in the above method for calculating the overall performance of the aircraft engine core, the calculating the performance of the core component includes:
considering the air leakage of the connection part between the flame tube and the turbine guide blade of the combustion chamber, and calculating the total pressure recovery coefficient of the combustion chamber;
considering the air leakage of the connection part between the flame tube and the turbine guide vane of the combustion chamber, and calculating the radial and circumferential unevenness of the temperature field at the outlet of the combustion chamber;
and (4) calculating the efficiency of the turbine by considering the air leakage of the connecting part between the combustor flame tube and the turbine guide vane.
In some optional embodiments, in the above method for calculating the overall performance of the core engine of the aircraft engine, the correcting a core engine flow balance equation based on the typical position air leakage specifically includes:
w 25 -w intermediate (II) -w Rotor -w Air leakage +w f ＝w 41 ；
Wherein the content of the first and second substances,
w 25 the air flow at the inlet of the compressor;
w intermediate (II) Introducing gas flow for the middle stage of the gas compressor;
w rotor For a turbine rotorThe airflow for the blades;
w air leakage The air leakage amount is the typical air leakage position of the core machine;
w f the fuel flow of the core engine;
w 41 is the amount of airflow at the inlet of the turbine rotor.
In some alternative embodiments, in the above method for calculating the overall performance of the aircraft engine core,
wherein the content of the first and second substances,
k is a gas physical property constant at the inlet of the compressor;
A 25 the area of the inlet of the compressor;
P 25 the total pressure at the inlet of the compressor;
q 25 the mass flow of the air flow at the inlet is compressed air;
T 25 the total temperature at the inlet of the compressor.
In some alternative embodiments, in the above method for calculating the overall performance of the aircraft engine core,
wherein the content of the first and second substances,
K g is the gas physical property constant at the inlet of the turbine rotor;
A 41 is the area at the inlet of the turbine rotor;
P 41 is the total pressure at the inlet of the turbine rotor;
q 41 is the mass flow of the gas flow at the inlet of the turbine rotor;
T 41 is the total temperature at the inlet of the turbine rotor.
In some optional embodiments, in the above method for calculating the overall performance of the core engine of the aircraft engine, the modifying the core machine work balance equation based on the typical position air leakage specifically includes:
wherein the content of the first and second substances,
T 41 the total temperature at the inlet of the turbine rotor;
T 25 the total temperature at the inlet of the compressor;
π c the expansion ratio of the compressor is;
k is a gas physical property constant at the inlet of the compressor;
η c to the compressor efficiency;
C p the specific constant pressure heat capacity of air;
C pg the specific constant pressure heat capacity of the fuel gas;
π T is the turbo-expansion ratio;
K g is the gas physical property constant at the inlet of the turbine rotor;
η T to turbine efficiency;
η machinery Mechanical efficiency;
w intermediate (II) Introducing gas flow for the middle stage of the gas compressor;
w rotor An airflow for turbine rotor blades;
w air leakage The air leakage amount of a typical air leakage position of the core machine;
w f is the core engine fuel flow.
The overall performance of the core machine is obtained through calculation by the method for calculating the overall performance of the core machine of the aircraft engine disclosed by the embodiment, and tests prove that the method has higher goodness of fit with the reality and can meet the requirements of designing and improving the support of the aircraft engine.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present invention in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present invention is not limited to those specific embodiments, and that equivalent changes or substitutions of the related technical features may be made by those skilled in the art without departing from the principle of the present invention, and those technical aspects after such changes or substitutions will fall within the scope of the present invention.
Claims (9)
1. An aircraft engine core machine overall performance calculation method is characterized by comprising the following steps:
identifying a typical leak location for the core machine;
calculating the air leakage of a typical air leakage position of the core machine;
analyzing the influence of the air leakage of the typical position on the performance of the core machine component, and further calculating the performance of the core machine component;
correcting a core machine flow balance equation and a work balance equation based on the air leakage of the typical position;
and calculating the overall performance of the core machine according to the performance of the core machine components, the flow balance equation of the core machine and the work balance equation.
2. The aircraft engine core gross performance calculation method according to claim 1,
typical leakage positions of the core engine comprise a connecting part between a compressor casing and a combustion chamber casing and a connecting part between a combustion chamber flame tube and a turbine guide blade.
3. The aircraft engine core gross performance calculation method according to claim 1,
the air leakage amount of the typical air leakage position of the core machine is obtained by a sealing test, and the method specifically comprises the following steps:
plugging a gas leakage position on the core machine except the typical gas leakage position of the gas leakage to be obtained;
measuring the air inlet flow and the air outlet flow of the core machine;
and subtracting the difference value of the air inlet flow and the air outlet flow of the core machine to obtain the air leakage of the typical air leakage position of the air leakage to be obtained.
4. The aircraft engine core gross performance calculation method according to claim 1,
the calculation of the air leakage amount of the typical air leakage position of the core machine is performed by deformation calculation, and specifically comprises the following steps:
calculating a cold state gap at a typical air leakage position of the air leakage to be obtained;
calculating a temperature field at a typical air leakage position of the air leakage to be obtained;
calculating a thermal state gap at the typical air leakage position of the air leakage to be obtained according to the cold state gap and the temperature field at the typical air leakage position of the air leakage to be obtained;
and calculating the air leakage at the typical air leakage position of the air leakage to be obtained according to the thermal state gap at the typical air leakage position of the air leakage to be obtained and the pneumatic boundary conditions of the thermal state gap.
5. The aircraft engine core gross performance calculation method according to claim 1,
the performance of the compute core machine component includes:
considering the air leakage of the connecting part between the flame tube and the turbine guide vane of the combustion chamber, and calculating the total pressure recovery coefficient of the combustion chamber;
considering the air leakage of the connection part between the flame tube and the turbine guide vane of the combustion chamber, and calculating the radial and circumferential unevenness of the temperature field at the outlet of the combustion chamber;
and (4) calculating the efficiency of the turbine by considering the air leakage of the connecting part between the combustor flame tube and the turbine guide vane.
6. The aircraft engine core gross performance calculation method according to claim 1,
the correction of the core machine flow balance equation based on the typical position air leakage specifically comprises the following steps:
w 25 -w intermediate (II) -w Rotor -w Leakage of gas +w f ＝w 41 ；
Wherein, the first and the second end of the pipe are connected with each other,
w 25 the air flow at the inlet of the air compressor;
w intermediate of Introducing gas flow for the middle stage of the gas compressor;
w rotor Airflow for turbine rotor blades;
w air leakage The air leakage amount is the typical air leakage position of the core machine;
w f the fuel flow of the core engine;
w 41 is the amount of airflow at the inlet of the turbine rotor.
7. The aircraft engine core gross performance calculation method according to claim 6,
wherein, the first and the second end of the pipe are connected with each other,
k is a gas physical property constant at the inlet of the compressor;
A 25 the area of the inlet of the compressor;
P 25 the total pressure at the inlet of the compressor;
q 25 the mass flow of the air flow at the inlet is compressed air;
T 25 the total temperature at the inlet of the compressor.
8. The aircraft engine core gross performance calculation method according to claim 6,
wherein the content of the first and second substances,
K g is the gas physical property constant at the inlet of the turbine rotor;
A 41 is the area at the inlet of the turbine rotor;
P 41 at the inlet of the turbine rotorTotal pressure;
q 41 is the mass flow of the gas flow at the inlet of the turbine rotor;
T 41 is the total temperature at the inlet of the turbine rotor.
9. The aircraft engine core gross performance calculation method according to claim 1,
the correcting method is characterized in that a core machine power balance equation is corrected based on the typical position air leakage, and specifically comprises the following steps:
wherein, the first and the second end of the pipe are connected with each other,
T 41 the total temperature at the inlet of the turbine rotor;
T 25 the total temperature at the inlet of the compressor;
π c the expansion ratio of the compressor is;
k is a gas physical property constant at the inlet of the compressor;
η c to the compressor efficiency;
C p the specific constant pressure heat capacity of air;
C pg the specific constant pressure heat capacity of the fuel gas;
π T is the turbo-expansion ratio;
K g is the gas physical property constant at the inlet of the turbine rotor;
η T to turbine efficiency;
η machine with a movable working part Mechanical efficiency;
w intermediate of Introducing gas flow for the middle stage of the gas compressor;
w rotor Airflow for turbine rotor blades;
w air leakage The air leakage amount is the typical air leakage position of the core machine;
w f is the core engine fuel flow.
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| CN115711747A (en) * | 2022-12-09 | 2023-02-24 | 中国航发沈阳发动机研究所 | Aircraft engine core performance calibration verification method |
| CN115753131A (en) * | 2022-12-09 | 2023-03-07 | 中国航发沈阳发动机研究所 | Verification method for high-temperature and high-pressure environment of core engine of aircraft engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115597882A (en) * | 2022-12-09 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Aerodynamic stability verification method for core engine of aircraft engine |
| CN115711747A (en) * | 2022-12-09 | 2023-02-24 | 中国航发沈阳发动机研究所 | Aircraft engine core performance calibration verification method |
| CN115753131A (en) * | 2022-12-09 | 2023-03-07 | 中国航发沈阳发动机研究所 | Verification method for high-temperature and high-pressure environment of core engine of aircraft engine |
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