CN115013164A - Method for determining resisting moment during starting of aircraft engine - Google Patents
Method for determining resisting moment during starting of aircraft engine Download PDFInfo
- Publication number
- CN115013164A CN115013164A CN202210558102.XA CN202210558102A CN115013164A CN 115013164 A CN115013164 A CN 115013164A CN 202210558102 A CN202210558102 A CN 202210558102A CN 115013164 A CN115013164 A CN 115013164A
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- Prior art keywords
- aircraft engine
- engine
- starting
- moment
- determining
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000007858 starting material Substances 0.000 claims abstract description 14
- 238000012937 correction Methods 0.000 claims abstract description 8
- 239000000446 fuel Substances 0.000 claims abstract description 5
- 230000001133 acceleration Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The application belongs to the technical field of determination of moment of resistance when an aero-engine is started, and particularly relates to a method for determining moment of resistance when an aero-engine is started, which comprises the following steps: cutting off fuel supply of the aircraft engine; starting a starter under the reference altitude and the reference environment temperature, driving the aircraft engine to operate by the starter, recording the rotating speed and time of the aircraft engine to operate, and fitting to obtain the reference resisting moment M when the aircraft engine is started c.0 (n), wherein n is the rotational speed at which the aircraft engine operates; for reference resisting moment M when starting aero-engine c.0 Correcting at different altitudes and ambient temperatures to obtain the resisting moment of the aircraft engine during starting
Wherein T is ambient temperature; t is a unit of 0 Is a reference ambient temperature; p is the pressure at the reference altitude; p 0 Is the pressure at the reference altitude; kqd is the aerodynamic drag correction factor; kmc is the coefficient of friction resistance.
Description
Technical Field
The application belongs to the technical field of determination of moment of resistance when an aero-engine is started, and particularly relates to a method for determining moment of resistance when the aero-engine is started.
Background
The starting of the aircraft engine is an accelerating process of the aircraft engine from 0 to a slow vehicle state, and the accelerating process of the aircraft engine speed depends on the output torque of a starter and the torque generated by the aircraft engine to overcome the resistance torque of the aircraft engine to do work.
The method is used for accurately determining the moment of resistance of the starting aircraft engine, is the basis of reliable design of the starting aircraft engine, and is mostly obtained by theoretical calculation based on sea level and normal temperature environment for determining the moment of resistance of the starting aircraft engine at present, and has the following defects:
1) the method is obtained by theoretical calculation, a large number of empirical formulas are applied, the technical experience of related technicians is relied on, and the obtained result has subjective arbitrariness and large deviation from the actual condition;
2) the results obtained without considering the change of the friction drag torque of the aircraft engine caused by the change of the ambient temperature and the influence of the viscosity of the lubricating oil, and without considering the change of the altitude and the influence of the atmospheric pressure and the change of the aerodynamic drag torque of the aircraft engine are not representative.
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 of determining drag torque at start of an aircraft engine to overcome or mitigate at least one aspect of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
a method of determining drag torque at start of an aircraft engine, comprising:
cutting off fuel supply of the aircraft engine;
starting a starter under the reference altitude and the reference environment temperature, driving the aircraft engine to operate by the starter, recording the rotating speed and time of the aircraft engine to operate, and fitting to obtain the reference resisting moment M when the aircraft engine is started c.0 (n), wherein n is the rotational speed at which the aircraft engine operates;
for reference resisting moment M when starting aero-engine c.0 Correcting at different altitudes and ambient temperatures to obtain the resisting moment of the aircraft engine during starting
Wherein T is ambient temperature; t is 0 Is a reference ambient temperature; p is the pressure at the reference altitude; p is 0 Is the pressure at the reference altitude; kqd is the aerodynamic drag correction factor; kmc is the coefficient of friction resistance.
According to at least one embodiment of the application, in the method for determining the starting-time resisting moment of the aircraft engine, the fitting obtains the reference resisting moment M of the aircraft engine at the starting time c.0 ＝a·n 2 And a is a coefficient of the reference resistance torque based on the rotating speed when the aircraft engine is started.
According to at least one embodiment of the application, in the method for determining the drag torque at start of an aircraft engine, the reference ambient temperature T 0 288.15K is taken.
According to at least one embodiment of the present application, in the method for determining drag torque at start of an aircraft engine described above, the pressure P at the reference altitude is 0 101.325KPa is taken.
According to at least one embodiment of the application, in the method for determining the drag torque of the aircraft engine during starting, the aerodynamic drag correction factor kqd is 0.5;
the coefficient of frictional resistance kmc is taken to be 1.
Drawings
FIG. 1 is a schematic diagram of a method for determining drag torque of an aircraft engine during starting according to 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 devices or elements must have specific orientations, be constructed and operated in specific orientations, and that when the absolute position of an 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 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.
In the process of accelerating the starting speed of the aircraft engine, the torque output by a starter and the torque generated by the aircraft engine overcome the resistance torque of the aircraft engine to do work, and the method specifically comprises the following steps:
M a ＝M T +M CT -M c ；
wherein,
M a starting an acceleration torque for the aircraft engine;
M T generating torque for the aircraft engine;
M CT outputting torque for a starter;
M c is the aircraft engine drag torque;
according to the above, during the starting speed acceleration of the aeroengine:
M CT ＝M a +M c -M T ；
when the aircraft engine is in cold operation, the fuel supply of the aircraft engine is cut off, the aircraft engine does not generate torque, the starter outputs torque to drive the aircraft engine to operate, the resistance torque of the aircraft engine is overcome to finish the acceleration process, and the balance rotating speed is maintained, wherein at the moment:
wherein:
η H the mechanical efficiency of the aircraft engine;
further, it is possible to obtain:
wherein:
j is the moment of inertia of the aircraft engine;
n is the rotating speed of the operation balance of the aircraft engine;
t is the time of the running balance of the aircraft engine;
the resistance moment M of the aero-engine can be obtained through fitting c ＝a·n 2 And a is a coefficient of the reference resistance torque based on the rotating speed when the aircraft engine is started.
In addition, experiments show that the change of the friction resistance moment of the aero-engine caused by the influence of the change of the environmental temperature on the viscosity of the lubricating oil and the change of the altitude, the influence of the change of the atmospheric pressure and the change of the aerodynamic resistance moment of the aero-engine can be corrected through the relative ratio of the temperature and the pressure and the corresponding coefficient.
In view of the above, an embodiment of the present application provides a method for determining a drag torque of an aircraft engine at start, including:
cutting off fuel supply of the aircraft engine;
starting a starter under the reference altitude and the reference environment temperature, driving the aircraft engine to operate by the starter, recording the rotating speed and time of the aircraft engine to operate, and fitting to obtain the reference resisting moment M when the aircraft engine is started c.0 (n), wherein n is the rotational speed at which the aircraft engine operates;
for reference resisting moment M when starting aero-engine c.0 Correcting at different altitudes and ambient temperatures to obtain the resisting moment of the aircraft engine during starting
Wherein T is ambient temperature; t is 0 Is a reference ambient temperature; p is the pressure at the reference altitude; p 0 Is the pressure at the reference altitude; kqd is the aerodynamic drag correction factor; kmc is the coefficient of friction resistance.
For the method for determining the moment of resistance of the aircraft engine during starting disclosed in the above embodiments, it can be understood by those skilled in the art that the design is to drive the aircraft engine to run in a cold state under the driving of the starter at the reference altitude and the reference ambient temperature thereof, and to obtain the reference moment of resistance M of the aircraft engine during starting through fitting c.0 And then correcting the altitude and the ambient temperature to obtain the resisting moment M when the aircraft engine is started c The change of the friction resistance moment of the aero-engine caused by the influence of the ambient temperature change on the viscosity of lubricating oil and the change of the aerodynamic resistance moment of the aero-engine caused by the influence of the altitude change and the atmospheric pressure are not considered, so that the accuracy is higher, and the aero-engine aerodynamic resistance moment can cover different altitudes and ambient temperatures.
In some optional embodiments, in the method for determining drag torque at start of an aircraft engine, the fitting may obtain a reference drag torque M at start of the aircraft engine c.0 ＝a·n 2 And a is a coefficient of the reference resisting moment based on the rotating speed when the aircraft engine is started.
In some optional embodiments, in the method for determining drag torque at start of an aircraft engine described above, the reference ambient temperature T 0 288.15K is taken.
In some alternative embodiments, in the above method for determining drag torque at start of an aircraft engine, the pressure P at the reference altitude is 0 101.325KPa is taken.
In some optional embodiments, in the method for determining the moment of resistance when the aircraft engine is started, the aerodynamic resistance correction coefficient kqd may be initially 0.5, the friction resistance coefficient kmc may be initially 1, and specific values may be obtained by driving the starter to perform cold-state operation for correction.
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 application 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 application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. A method of determining drag torque at start-up of an aircraft engine, comprising:
cutting off fuel supply of the aircraft engine;
starting a starter under the reference altitude and the reference environment temperature, driving the aircraft engine to operate by the starter, recording the rotating speed and time of the aircraft engine to operate, and fitting to obtain the reference resisting moment M when the aircraft engine is started c.0 (n), wherein n is the rotational speed at which the aircraft engine operates;
for reference resisting moment M when starting aero-engine c.0 Correcting at different altitudes and ambient temperatures to obtain the resisting moment of the aircraft engine during starting
Wherein T is ambient temperature; t is 0 Is a reference ambient temperature; p is the pressure at the reference altitude; p 0 Is the pressure at the reference altitude; kqd is the aerodynamic drag correction factor; kmc is a frictional resistance systemAnd (4) counting.
2. The method of determining drag torque at startup of an aircraft engine of claim 1,
the fitting obtains a reference resisting moment M when the aircraft engine is started c.0 ＝a·n 2 And a is a coefficient of the reference resistance torque based on the rotating speed when the aircraft engine is started.
3. The method of determining drag torque at startup of an aircraft engine of claim 1,
reference ambient temperature T 0 288.15K is taken.
4. The method of determining drag torque at startup of an aircraft engine of claim 1,
pressure at reference altitude P 0 101.325KPa is taken.
5. The method of determining drag torque at startup of an aircraft engine of claim 1,
the pneumatic resistance correction coefficient kqd is 0.5;
the coefficient of frictional resistance kmc is taken to be 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210558102.XA CN115013164A (en) | 2022-05-19 | 2022-05-19 | Method for determining resisting moment during starting of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210558102.XA CN115013164A (en) | 2022-05-19 | 2022-05-19 | Method for determining resisting moment during starting of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115013164A true CN115013164A (en) | 2022-09-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210558102.XA Pending CN115013164A (en) | 2022-05-19 | 2022-05-19 | Method for determining resisting moment during starting of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115013164A (en) |
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2022
- 2022-05-19 CN CN202210558102.XA patent/CN115013164A/en active Pending
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Inventor after: Guo Haihong Inventor after: Wang Haibo Inventor after: Liu Yajun Inventor after: Jin Hai Inventor after: Xing Yang Inventor before: Guo Haihong Inventor before: Liu Yajun Inventor before: Jin Hai Inventor before: Xing Yang |