CN114996978B - Method and device for calculating airflow parameters at inlet of combustion chamber of turbofan engine - Google Patents

Method and device for calculating airflow parameters at inlet of combustion chamber of turbofan engine Download PDF

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CN114996978B
CN114996978B CN202210935090.8A CN202210935090A CN114996978B CN 114996978 B CN114996978 B CN 114996978B CN 202210935090 A CN202210935090 A CN 202210935090A CN 114996978 B CN114996978 B CN 114996978B
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turbofan engine
inlet
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windmill
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CN114996978A (en
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尚明智
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Xi'an Chengli Aviation Manufacturing Co ltd
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Abstract

The invention provides a method and a device for calculating inlet airflow parameters of a combustion chamber of a turbofan engine, wherein the method comprises the step of acquiring the air pressure P far ahead of the engine with different flight heights and flight Mach numbers in a standard air gauge according to the flight heights and the flight Mach numbers which are required to be calculated H And air temperature T H (ii) a Acquiring a windmill characteristic value of the turbofan engine in a windmill state; the windmill characteristic numerical values comprise the compression ratio and the temperature rise ratio of the gas compressor and the density flow ratio of the engine; and calculating the inlet airflow parameter of the combustion chamber of the turbofan engine according to the windmill characteristic value. According to the calculation method and the calculation device provided by the embodiment of the invention, the exact data of the inlet airflow parameters of the combustion chamber of the turbofan engine in the windmill state is obtained according to the statistic data of the windmill characteristics of the turbofan engine, so that the inlet airflow parameters of the combustion chamber of the turbofan engine are estimated.

Description

Method and device for calculating inlet airflow parameters of combustion chamber of turbofan engine
Technical Field
The invention relates to the technical field of aviation, in particular to a method and a device for calculating inlet airflow parameters of a combustion chamber of a turbofan engine.
Background
The determination of the basic size of the combustion chamber and the high altitude ignition simulation test of the combustion chamber require parameters such as inlet air pressure, inlet air temperature and air flow through the combustion chamber in a high altitude windmill condition. Therefore, the calculation of the inlet parameters of the combustion chamber in the windmill state is an indispensable calculation item in the design of the combustion chamber. However, since the characteristics of the compressor and the turbine at low rotation speed are difficult to obtain, accurate calculation of the inlet parameters of the combustion chamber in a windmill state is difficult to achieve.
Disclosure of Invention
In order to solve the above problems, embodiments of the present invention provide a method and an apparatus for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine.
In a first aspect, an embodiment of the present invention provides a method for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine, including:
in a standard atmosphere meter, different flight altitudes and flight mach numbers are obtained according to the flight altitude and the flight mach number which are calculated as requiredMach-number engine far-ahead air pressure P H And air temperature T H ；
Acquiring a windmill characteristic value of the turbofan engine in a windmill state;
the windmill characteristic numerical values comprise the compression ratio and the temperature rise ratio of the gas compressor and the density flow ratio of the engine;
calculating an inlet airflow parameter of the turbofan engine combustion chamber according to the windmill characteristic value; wherein the content of the first and second substances,
according to the flight selected M H The compression ratio of the compressor of the turbofan engine in a windmill state is as follows:
∏ K = （0.4～0.6）M 4 H -（1～2）M 3 H + （2.5～3）M 2 H -（2～2.5）M H +1；
the temperature rise ratio of the compressor of the turbofan engine in a windmill state is as follows:
τ K = 1～2；
a density flow ratio of the turbofan engine in a windmill state:
q 3 = （1～1.5）M H -0.1；
and drawing a carpet graph of the inlet airflow parameters of the combustion chamber of the turbofan engine in a windmill state according to the inlet airflow parameters of the combustion chamber of the turbofan engine.
In a second aspect, an embodiment of the present invention further provides an apparatus for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine, including:
a parameter acquisition module used for acquiring the air pressure P far ahead of the engine with different flight altitudes and flight Mach numbers according to the flight altitude and the flight Mach number calculated by the requirement in the standard atmosphere meter H And air temperature T H ；
The characteristic acquisition module is used for acquiring a windmill characteristic value of the turbofan engine in a windmill state; the windmill characteristic numerical values comprise the compression ratio and the temperature rise ratio of the gas compressor and the density flow ratio of the engine;
the parameter calculation module is used for calculating the inlet airflow parameter of the combustion chamber of the turbofan engine according to the windmill characteristic value; wherein, the first and the second end of the pipe are connected with each other,
according to the flight selected M H The compression ratio of the compressor of the turbofan engine in a windmill state is as follows:
∏ K = （0.4～0.6）M 4 H - （1～2）M 3 H + （2.5～3）M 2 H -（2～2.5）M H +1；
the temperature rise ratio of the compressor of the turbofan engine in a windmill state is as follows:
τ K = 1～2；
a density flow ratio of the turbofan engine in a windmill state:
q3= （1～1.5）M H -0.1；
and the carpet drawing module is used for drawing a carpet drawing of the inlet airflow parameters of the combustion chamber of the turbofan engine under the windmill state according to the inlet airflow parameters of the combustion chamber of the turbofan engine.
According to the method and the device for calculating the inlet airflow parameters of the combustion chamber of the turbofan engine, the exact data of the inlet airflow parameters of the combustion chamber of the turbofan engine in the windmill state is obtained according to the statistic data of the windmill characteristics of the turbofan engine, so that the inlet airflow parameters of the combustion chamber of the turbofan engine are estimated, and the influence of the inlet airflow parameters of the combustion chamber of the turbofan engine on the high-altitude ignition test result of the combustion chamber is reduced.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a flow chart illustrating a method for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine according to an embodiment of the invention;
FIG. 2 illustrates a carpet map of turbofan engine combustor inlet airflow parameters provided by an embodiment of the present invention;
fig. 3 is a schematic structural diagram illustrating a device for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine according to an embodiment of the invention.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the determination of the basic size of the combustion chamber and in the high-altitude ignition simulation test of the combustion chamber, parameters such as the inlet air pressure, the inlet air temperature and the air flow passing through the combustion chamber of the combustion chamber in a high-altitude windmill state are needed, so that the calculation of the inlet parameters of the combustion chamber in the windmill state is an indispensable calculation item in the design of the combustion chamber. Because the characteristics of the compressor and the turbine at low rotating speed are difficult to obtain, accurate calculation of the air flow parameters at the inlet of the combustion chamber under the windmill state is difficult to complete.
The windmill state of the engine refers to the state that the rotating speed of the engine is stable and unchanged under certain flying height and flying Mach number after the engine is stopped in the air. At the moment, the work of the engine is maintained by the air impulse at the inlet of the engine, the front stages of the air compressor are in a turbine state, the rear stages of the air compressor are in an air compressor state, and when the flying Mach number exceeds a certain value (called critical flying Mach number), the pressure and the temperature of the air compressor are increased. We refer to this result as the "windmill effect".
The windmill characteristics are only dependent on the flight mach number and independent of the flight altitude.
In the research of the embodiment of the invention, no matter what type of air compressor, how high the design level of the air compressor is and how the performance parameters of the air compressor are, the air compressor is far away from the design point in the windmill state, so the performance levels of the air compressor are not greatly different, and the air compressor has approximately the same statistical rules. In other words, the engine has versatility in the windmill state, as to the pressure increase ratio and temperature increase ratio of the compressor, and the relationship between the dense flow flowing through the engine and the flight mach number (i.e., the windmill characteristics). Thus, it is possible to use the windmill characteristics common to turbofan engines to calculate combustor inlet parameters, with an acceptable accuracy from an engineering standpoint.
In the past, when the pneumatic parameters of the combustion chamber inlet in a windmill state are calculated, calculation methods of various versions are adopted, and an exact conclusion cannot be given to the engineering use value of a calculation result, so that the influence on the size design of the combustion chamber and the high-altitude ignition test result of the combustion chamber is large.
As shown in FIG. 1, the embodiment of the present invention provides a simple method for calculating the inlet airflow parameters of the combustion chamber under windmilling condition with engineering practical value according to the statistical data of the windmilling characteristics of the turbofan engine.
Step S101: in a standard air gauge, according to calculation domain parameters needing to be calculated, such as flight altitude and flight Mach number, the air pressure P far ahead of an engine at different flight altitudes and flight Mach numbers is found out H And air temperature T H ；
Step S103: according to selected flight M H Number, calculated as follows:
calculating the compression ratio of a compressor of the turbofan engine in a windmill state:
∏ K = （0.4～0.6）M 4 H - （1～2）M 3 H + （2.5～3）M 2 H -（2～2.5）M H +1；
calculating the temperature rise ratio of the air compressor of the turbofan engine in a windmill state:
τ K = 1～2；
calculating the density flow ratio of the turbofan engine in a windmill state:
q 3 = （1～1.5）M H -0.1；
Figure 321835DEST_PATH_IMAGE001
；
q design 3 : a dense flow function of the turbofan engine in a design state;
q 3 windmill : a dense flow function of the turbofan engine in a windmill state;
P 3 design of : combustor inlet air pressure of a turbofan engine at design conditions;
P 3 windmill : inlet air pressure of a combustion chamber of a turbofan engine in a windmill state;
g: mass air flow through the turbofan engine;
Figure 176658DEST_PATH_IMAGE002
: the combination parameter of the engine content air flow and the combustion chamber inlet air temperature of the turbofan engine in a windmill state;
Figure 894079DEST_PATH_IMAGE003
: the combination parameter of the engine content air flow and the combustion chamber inlet air temperature of the turbofan engine in the design state;
step S105: the turbofan engine combustor inlet airflow parameters include combustor inlet air pressure, calculated combustor inlet air pressure:
P 3 =P H *σ air inlet channel *∏ K (ii) a Wherein, the first and the second end of the pipe are connected with each other,
here the loss of the engine intake: sigma Air inlet channel =1.0；
P H : far forward air pressure of a turbofan engine combustor;
step S107: the turbofan engine combustor inlet airflow parameters include combustor inlet air temperature, calculated combustor inlet air temperature: t is a unit of 3 =T H *τ K ；
T H : far forward air temperature of a turbofan engine combustor;
step S109: the inlet airflow parameters of the combustion chamber of the turbofan engine comprise the inlet air density flow of the combustion chamber, and the inlet air density flow of the combustion chamber is calculated as follows: g 3 =q 3 *q 3 design of ；
Step S111: the turbofan engine combustor inlet airflow parameters include combustor inlet airflow flow, and the combustor inlet airflow flow is calculated as follows:
G=m* P 4 * G 3 *F 4 / T 4 0.5 (ii) a Wherein the content of the first and second substances,
m = constant 0.3965;
p4 ≈ P3, where combustor losses are neglected;
t4= T3, no combustion in the combustion chamber;
f4: the area of a spray pipe ring of the high-pressure turbine primary guider;
step S113: the above calculation results were used to plot a carpet map of the combustion chamber inlet airflow parameters for the windmill condition of the turbofan engine, as shown in fig. 2.
According to the method for calculating the inlet airflow parameters of the combustion chamber of the turbofan engine, the exact data of the inlet airflow parameters of the combustion chamber of the turbofan engine in the windmill state is obtained according to the statistical data of the windmill characteristics of the turbofan engine, so that the inlet airflow parameters of the combustion chamber of the turbofan engine are estimated, and the influence of the inlet airflow parameters of the combustion chamber of the turbofan engine on the high-altitude ignition test result of the combustion chamber is reduced.
As will be appreciated by one skilled in the art, embodiments of the present invention may be embodied as methods, apparatus, electronic devices, and computer-readable storage media. Thus, embodiments of the invention may be embodied in the form of: entirely hardware, entirely software (including firmware, resident software, micro-code, etc.), a combination of hardware and software. Furthermore, in some embodiments, embodiments of the invention may also be implemented in the form of a computer program product in one or more computer-readable storage media having computer program code embodied in the storage medium.
The computer-readable storage media described above may take any combination of one or more computer-readable storage media. The computer-readable storage medium includes: an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of the computer readable storage medium include: a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only Memory (ROM), an erasable programmable read-only Memory (EPROM), a Flash Memory (Flash Memory), an optical fiber, a compact disc read-only Memory (CD-ROM), an optical storage device, a magnetic storage device, or any combination thereof. In embodiments of the invention, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, device, or apparatus.
The computer program code embodied on the computer readable storage medium may be transmitted using any appropriate medium, including: wireless, wire, fiber optic cable, radio Frequency (RF), or any suitable combination thereof.
Computer program code for carrying out operations for embodiments of the present invention may be written in one or more programming languages, including an object oriented programming language such as: java, smalltalk, C + +, and also include conventional procedural programming languages, such as: c or a similar programming language. The computer program code may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the case of a remote computer, the remote computer may be over any of a variety of networks, including: a Local Area Network (LAN) or a Wide Area Network (WAN), which may be connected to the user's computer, may be connected to an external computer.
Embodiments of the present invention are described below with reference to flowchart illustrations and/or block diagrams of methods, apparatus, electronic devices, and computer-readable storage media according to embodiments of the invention.
It will be understood that each block of the flowchart illustrations and/or block diagrams, and combinations of blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer-readable program instructions. These computer-readable program instructions may be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions/acts specified in the flowchart and/or block diagram block or blocks.
These computer-readable program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing apparatus to function in a particular manner. Thus, the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means which implement the function/act specified in the flowchart and/or block diagram block or blocks.
The computer readable program instructions may also be loaded onto a computer, other programmable data processing apparatus, or other devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions/acts specified in the flowchart and/or block diagram block or blocks.
The embodiments of the present invention will be described below with reference to the drawings.
Fig. 3 is a schematic structural diagram of an apparatus for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine according to an embodiment of the invention, as shown in fig. 3:
the method comprises the following steps: a parameter obtaining module 10, configured to obtain, in a standard air gauge, air pressure P far ahead of an engine with different flight altitudes and flight mach numbers according to the flight altitude and flight mach numbers that need to be calculated H And air temperature T H ；
A characteristic acquisition module 20 for acquiring a windmill characteristic value of the turbofan engine in a windmill state; the windmill characteristic numerical values comprise the compression ratio and the temperature rise ratio of the gas compressor and the density flow ratio of the engine;
a parameter calculating module 30, configured to calculate an inlet airflow parameter of the turbofan engine combustion chamber according to the windmill characteristic value; wherein, the first and the second end of the pipe are connected with each other,
according to the flight selected M H The compression ratio of the compressor of the turbofan engine in a windmill state is as follows:
∏ K = （0.4～0.6）M 4 H - （1～2）M 3 H + （2.5～3）M 2 H -（2～2.5）M H +1；
the temperature rise ratio of the compressor of the turbofan engine in a windmill state is as follows:
τ K = 1～2；
a density flow ratio of the turbofan engine in a windmill state:
q 3 = （1～1.5）M H -0.1；
and the carpet drawing module 40 is used for drawing a carpet drawing of the inlet airflow parameter of the combustion chamber of the turbofan engine under the windmill state according to the inlet airflow parameter of the combustion chamber of the turbofan engine.
Wherein, in the parameter calculation module, the turbofan engine combustor inlet airflow parameters include a combustor inlet air pressure:
P 3 =P H *σ air inlet channel *∏ K (ii) a Wherein the content of the first and second substances,
loss of engine air intake: sigma Air inlet channel =1.0 。
Wherein, in the parameter calculation module 30, the turbofan engine combustor inlet airflow parameters include a combustor inlet air temperature:
T 3 =T H *τ K 。
wherein, in the parameter calculation module 30, the turbofan engine combustor inlet airflow parameters include combustor inlet airflow density:
G 3 =q 3 *q design 3 。
Wherein, in the parameter calculation module 30, the turbofan engine combustor inlet airflow parameter includes a combustor inlet airflow rate:
G=m* P 4 * G 3 *F 4 / T 4 0.5 (ii) a Wherein, the first and the second end of the pipe are connected with each other,
m = constant 0.3965;
p4 ≈ P3, where combustor losses are neglected;
t4= T3, no combustion in the combustion chamber;
f4: nozzle ring area of the high pressure turbine primary guide.
According to the device for calculating the inlet airflow parameters of the combustion chamber of the turbofan engine, the exact data of the inlet airflow parameters of the combustion chamber of the turbofan engine in the windmill state is obtained according to the statistical data of the windmill characteristics of the turbofan engine, so that the inlet airflow parameters of the combustion chamber of the turbofan engine are estimated, and the influence of the inlet airflow parameters of the combustion chamber of the turbofan engine on the high-altitude ignition test result of the combustion chamber is reduced.
The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the technical scope of the present invention, and the technical scope of the present invention is covered by the modifications or alternatives. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.

Claims (10)

1. A method for calculating inlet airflow parameters of a combustion chamber of a turbofan engine is characterized by comprising the following steps:
in a standard air gauge, acquiring the air pressure P far ahead of an engine with different flight heights and flight Mach numbers according to the flight heights and the flight Mach numbers which are calculated as required H And air temperature T H ；
Acquiring a windmill characteristic value of the turbofan engine in a windmill state;
the windmill characteristic numerical values comprise the compression ratio and the temperature rise ratio of the gas compressor and the density flow ratio of the engine;
calculating an inlet airflow parameter of the turbofan engine combustion chamber according to the windmill characteristic value;
wherein the turbofan engine combustor inlet airflow parameters include: inlet air pressure, inlet air temperature, inlet air density flow and inlet airflow flow of the combustion chamber;
according to selected flight M H The compression ratio of the compressor of the turbofan engine in the windmill state is as follows:
∏ K = （0.4～0.6）M 4 H - （1～2）M 3 H + （2.5～3）M 2 H -（2～2.5）M H +1；
the temperature rise ratio of the compressor of the turbofan engine in a windmill state is as follows:
τ K = 1～2；
a density flow ratio of the turbofan engine in a windmill state:
q 3 = （1～1.5）M H -0.1；
and drawing a carpet graph of the inlet airflow parameters of the combustion chamber of the turbofan engine in a windmill state according to the inlet airflow parameters of the combustion chamber of the turbofan engine.
2. The method of claim 1, wherein the combustor inlet air pressure is:
P 3 =P H *σ air inlet channel *∏ K (ii) a Wherein, the first and the second end of the pipe are connected with each other,
loss of engine inlet: sigma Air inlet channel =1.0 。
3. The method of claim 2, wherein the combustor inlet air temperature is:
T 3 =T H *τ K 。
4. the method of claim 3, wherein the combustor inlet air dense flow:
G 3 =q 3 *q design 3 Wherein q is Design 3 Is the dense flow function of the turbofan engine under the design condition.
5. The method of claim 4, wherein the combustor inlet airflow rate is:
G=m* P 4 * G 3 *F 4 / T 4 0.5 (ii) a Wherein, the first and the second end of the pipe are connected with each other,
m = constant 0.3965;
p4 ≈ P3, where combustor losses are neglected;
t4= T3, no combustion in the combustion chamber;
f4: nozzle ring area of the high pressure turbine primary guide.
6. An apparatus for calculating an inlet airflow parameter of a combustion chamber of a turbofan engine, comprising:
a parameter obtaining module used for obtaining the air pressure P far ahead of the engine with different flight heights and flight Mach numbers according to the flight heights and the flight Mach numbers which are calculated in the standard air gauge H And air temperature T H ；
The characteristic acquisition module is used for acquiring a windmill characteristic value of the turbofan engine in a windmill state; the windmill characteristic numerical values comprise the compression ratio and the temperature rise ratio of the gas compressor and the density flow ratio of the engine;
the parameter calculation module is used for calculating the inlet airflow parameter of the combustion chamber of the turbofan engine according to the windmill characteristic value;
wherein the turbofan engine combustor inlet airflow parameters include: inlet air pressure, inlet air temperature, inlet air density flow and inlet airflow flow of the combustion chamber;
according to the flight selected M H The compression ratio of the compressor of the turbofan engine in a windmill state is as follows:
∏ K = （0.4～0.6）M 4 H - （1～2）M 3 H + （2.5～3）M 2 H -（2～2.5）M H +1；
the temperature rise ratio of the compressor of the turbofan engine in a windmill state is as follows:
τ K = 1～2；
a density flow ratio of the turbofan engine in a windmill state:
q 3 = （1～1.5）M H -0.1；
and the carpet drawing module is used for drawing a carpet drawing of the inlet airflow parameters of the combustion chamber of the turbofan engine under the windmill state according to the inlet airflow parameters of the combustion chamber of the turbofan engine.
7. The apparatus of claim 6, wherein in the parameter calculation module, the combustor inlet air pressure is:
P 3 =P H *σ air inlet channel *∏ K (ii) a Wherein, the first and the second end of the pipe are connected with each other,
loss of engine inlet: sigma Air inlet channel =1.0 。
8. The apparatus of claim 7, wherein in the parameter calculation module, the combustor inlet air temperature is:
T 3 =T H *τ K 。
9. the apparatus of claim 7, wherein in the parameter calculation module, the combustor inlet air dense flow:
G 3 =q 3 *q 3 design of Wherein q is 3 design of Is the density flow function of the turbofan engine under the design condition.
10. The apparatus of claim 7, wherein in the parameter calculation module, the combustor inlet airflow rate is:
G=m* P 4 * G 3 *F 4 / T 4 0.5 (ii) a Wherein, the first and the second end of the pipe are connected with each other,
m = constant 0.3965;
p4 ≈ P3, where combustor losses are neglected;
t4= T3, no combustion in the combustion chamber;
f4: nozzle ring area of the high pressure turbine primary guide.
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