CN113266473A - Method for measuring starting resistance moment of aero-engine under non-loading condition - Google Patents
Method for measuring starting resistance moment of aero-engine under non-loading condition Download PDFInfo
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- CN113266473A CN113266473A CN202110609249.2A CN202110609249A CN113266473A CN 113266473 A CN113266473 A CN 113266473A CN 202110609249 A CN202110609249 A CN 202110609249A CN 113266473 A CN113266473 A CN 113266473A
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Engineering & Computer Science (AREA)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the technical field of engine tests, and particularly relates to a method for measuring starting resistance moment of an aero-engine under a non-loading condition. The air turbine starter is driven to rotate by the air source control device, the engine is driven to start by the air turbine starter, and the power transmission shaft is provided with a torque measuring device; calibrating the air source condition of the starting process of the engine, and carrying out an engine starting test by utilizing the calibrated air source condition; within the time period from the successful starting of the engine to the completion of the starting, acquiring the residual torque of the power transmission shaft and acquiring the engine rotating speeds of a plurality of corresponding time nodes; an engine starting drag torque is determined. This application is through the measurement to the moment of resistance of a plurality of time nodes of engine starting process, can be more accurate acquire engine starting process test data, experimental easy operation is convenient for realize, can obtain real aeroengine starting moment of resistance measuring result.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a method for measuring starting resistance moment of an aero-engine under a non-loading condition.
Background
Aircraft engines, one of the most important devices of an aircraft, are capable of providing the thrust necessary for the flight of the aircraft. The aero-engine is transited from a static state to a working state, the aero-engine can be effectively started only by the aid of the driving of the starter, and the output torque of the starter needs to overcome the influence of the resistance torque of the aero-engine. Therefore, the drag torque during the starting process of the aircraft engine has direct influence on the type selection and starting performance of the starter. In the traditional model design process, the starting system is taken as an important assessment item and is specified in GJB 241A-2010, GJB2187A-2015 and HB 6630-92 in detail.
In the design process of the conventional starting system of the aircraft engine, the design of the relevant starting system is developed mainly by calibrating the output torque characteristic of a starter and applying a mode of combining engineering experience and test, and the design method mainly has the following difficulties and problems in several aspects:
1. because the starting process of the aircraft engine is a complex dynamic process, the structural parameters of internal geometric components, the working environment of engine starting, the efficiency of rotor components of the engine and the like all influence the resisting moment in the starting process of the engine, and how to accurately calibrate the starting resisting moment of the engine so as to obtain the starting load characteristics of the engine, a starter and an airplane is a complex engineering problem;
2. the gas turbine starter is adopted for starting the aircraft engine in the prior art, because the output torque of the starter can be changed in a certain range by adjusting the oil supply flow through the oil supply main pump, the starting test needs to be carried out through the starters with different power magnitudes in the test process, the resource consumption is high, and the test period and the cost are high;
3. the relation between the starting time of the engine and the residual torque cannot be accurately given in the starting process of the engine, the starting time has a crucial relation to the mission starting of the airplane, the starters are screened in the similar engine analogy mode in the previous model design process, once the starters are selected, the starting time is determined by the starters, and the relation between the starting time and the starting residual power cannot be found through forward design;
4. after the aircraft engine is used for a long time, the performance of components of the engine can be degraded, and the starting resistance moment of the engine can also be changed, particularly after the aircraft engine is repaired. Because part of components are replaced, the factory inspection after the overhaul is mainly the basic routine inspection, and the difference between the starting resistance moment of the engine after the overhaul and the original state cannot be accurately obtained by adopting the traditional measuring method;
disclosure of Invention
In order to solve the above problems, the present application provides a method for measuring starting moment of drag of an aircraft engine under an unloaded condition, which mainly comprises:
step S1, driving a turbine starter to rotate through an air source control device, driving a gear shaft of an accessory transmission device to rotate through the turbine starter, and connecting an engine transmission device through a power transmission shaft so as to drive the engine transmission device to start, wherein a torque measuring device is arranged on the power transmission shaft;
step S2, calibrating the air source condition of the engine starting process, and performing an engine starting test by using the calibrated air source condition;
step S3, obtaining total residual torque values of the engine at different rotating speeds from starting to finishing starting, recording the environmental pressure as p0, and recording the air source flow as Wa air, the total pressure as pt air and the total temperature as Tt air;
step S4, step S4, and determination of starting resistance moment M of aeroengineT＝MGeneral assembly-Mst。
Wherein M isstFor turbo starter output torque:
wherein, CpIs a constant number ηAir (a)Efficiency of the air line system (including control valve) (. eta.)ATSFor turbo-starter efficiency, ptATSThe total pressure at the inlet of the turbine starter is eta, and the efficiency of a transmission system is etaTransmission gear。
Preferably, in step S2, an engine start control plan and timing are acquired, and an engine start test is performed according to the engine start control plan and timing.
Preferably, in step S2, an engine start control plan and timing are acquired, and an engine start test is performed according to the engine start control plan and timing.
Preferably, the air supply conditions for the calibration engine starting process in step S2 include flow, temperature, pressure, air turbine starter parameters, air line and control valve parameters, and torque measurement device parameters of the calibration air supply.
Preferably, the turbo starter is an air turbo starter.
Preferably, in step S4, N M are calculatedTAnd fitting a functional relation graph of the starting resistance torque of the engine and the rotating speed of the engine.
Preferably, M is removed before step S4TOutlier points in the values.
Preferably, in step S4, N is 80-120.
The resistance torque of the engine is directly measured through tests, the output torque characteristic of the air turbine starter is mainly that the energy of air is converted into mechanical shaft power, the measurement precision is high, oil supply and control for the air turbine starter are not needed, the exhaust gas temperature of the air turbine starter is far lower than the exhaust gas emission temperature of the gas turbine starter, the test operation is simple and convenient to achieve, and a real engine starting resistance torque result can be obtained.
This application is through the measurement to the moment of resistance of a plurality of time nodes of engine starting process, can be more accurate acquire engine starting process test data, experimental easy operation is convenient for realize, can obtain real aeroengine starting moment of resistance measuring result.
Drawings
FIG. 1 is a flow chart of a method for measuring starting drag torque of an aircraft engine under an unloaded condition.
FIG. 2 is a flow chart of an aircraft engine starting drag torque measurement test under unloaded conditions.
FIG. 3 is a schematic diagram of an aviation conventional engine starting resistance moment measurement test environment under an unloaded condition.
FIG. 4 is a schematic view of an aircraft engine starting drag torque measurement test environment under an unloaded condition.
FIG. 5 is a graphical illustration of aircraft engine starting drag torque versus rotational speed under unloaded conditions.
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 accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The invention provides a method for measuring starting resistance moment of an aeroengine under the condition of no loading, which mainly comprises the following steps as shown in figure 1:
step S1, driving a turbine starter to rotate through an air source control device, driving a gear shaft of an accessory transmission device to rotate through the turbine starter, and connecting an engine transmission device through a power transmission shaft so as to drive the engine transmission device to start, wherein a torque measuring device is arranged on the power transmission shaft;
step S2, calibrating the air source condition of the engine starting process, and performing an engine starting test by using the calibrated air source condition;
step S3, obtaining the total residual torque value M of the engine at different rotating speeds n from starting to finishing of startingGeneral assemblyRecording the ambient pressure p0Air source flow Wa airTotal pressure pt airTotal temperature Tt air；
Step S4, determining the starting resistance moment M of the aeroengineT＝MGeneral assembly-Mst。
Wherein M isstFor turbo starter output torque:
wherein, CpConstant, air line system (including control valve) efficiency ηAir (a)Efficiency η of turbo-starterATSTotal pressure at the entrance of the turbo starter is ptATSTransmission system efficiency of etaTransmission gear。
In some alternative embodiments, in step S2, an engine start control plan and timing are acquired, and an engine start test is performed according to the engine start control plan and timing.
In some alternative embodiments, the air supply conditions for the calibration engine starting process in step S2 include flow, temperature, pressure, air turbine starter parameters, air line and control valve parameters, and torque measurement device parameters of the calibration air supply.
In some alternative embodiments, the turbo starter is an air turbo starter.
In some alternative embodiments, in step S4, N M are calculatedTAnd fitting a functional relation graph of the starting resistance moment of the aircraft engine and the rotating speed of the engine.
In some alternative embodiments, at step (ii), the method further comprisesBefore S4, M is removedTOutlier points in the values.
In some optional embodiments, in step S4, N is 80 to 120.
The following examples are given.
The first step is as follows: starting a certain type of engine under the condition of a fixed air source for 36s, and recording the total intake pressure of the engine under the condition of the air source as pt air450kPa, ambient pressure pt0101kpa, pressure drop ratio piC4.455, total intake air temperature Tt air483K, inlet flow Wat air1.1kg/s, the total power Ptotal of the air inlet source is 185.51 kw;
the second step is that: obtaining the total residual torque M of the engine when the rotating speed of the engine is 3000rpm through a torque sensorGeneral assembly＝Mst+MT＝196.6N.m
The third step: according to
ηAir (a)Is calibrated on the bench for the inherent loss of the air pipeline system and is 0.9 etaATSThe efficiency at 3000rpm of the corresponding engine speed is found to be 0.63 by looking up the table; etaTransmission gearThe efficiency of the air turbine starter is calibrated to be 0.98 through a bench test, so that the output power P of the air turbine starter can be obtained when the engine speed is 3000rpmATS103.08kw, the output torque M of the air turbine starter at an engine speed of 3000rpm can be obtained according to M9549P/nst＝9549*103.08/3000＝328.1N.m；
The fourth step: according to MGeneral assembly＝Mst+MTThe total torque for engine start obtained by the third step is 196.6N.m, then MT＝MGeneral assembly-Mst＝196.6-328.1＝-131.5N.m；
The fifth step: the resistance torque characteristics at different rotating speeds can be repeated in the processes from the second step to the fourth step, the N value area is 100, outliers in the outliers are removed, data fitting is carried out on the torque characteristics at different rotating speeds, and the starting resistance torque characteristics of the engine at different rotating speeds can be obtained.
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 (7)
1. A method for measuring starting resistance torque of an aircraft engine under an unloaded condition is characterized by comprising the following steps:
step S1, driving a turbine starter to rotate through an air source control device, driving a gear shaft of an accessory transmission device to rotate through the turbine starter, and connecting an engine transmission device through a power transmission shaft so as to drive the engine transmission device to start, wherein a torque measuring device is arranged on the power transmission shaft;
step S2, calibrating the air source condition of the engine starting process, and performing an engine starting test by using the calibrated air source condition;
step S3, obtaining the total residual torque value M of the engine at different rotating speeds n from starting to finishing of startingGeneral assemblyRecording the ambient pressure p0Air source flow Wa airTotal pressure pt airTotal temperature Tt air；
Step S4, determining the starting resistance moment M of the aeroengineT＝MGeneral assembly-Mst。
Wherein M isstFor turbo starter output torque:
wherein, CpIs a constant number ηAir (a)For efficiency of the air line system, ηATSFor turbo-starter efficiency, ptATSThe total pressure at the inlet of the turbine starter is eta, and the efficiency of a transmission system is etaTransmission gear。
2. The method for measuring aircraft engine starting drag torque under unloaded conditions as claimed in claim 1, wherein in step S2, an engine starting control plan and timing are obtained, and an engine starting test is performed according to the engine starting control plan and timing.
3. The method for measuring aircraft engine starting drag torque under unloaded conditions as claimed in claim 2, wherein in step S2, the air supply conditions for the calibration engine starting process include flow, temperature, pressure, air turbine starter parameters, air line and control valve parameters, and torque measuring device parameters of the calibration air supply.
4. The method of measuring aircraft engine starting drag torque under unloaded conditions of claim 1, wherein said turbo starter is an air turbo starter.
5. The method for measuring aircraft engine starting drag torque under unloaded condition as claimed in claim 1, wherein in step S4, N M numbers of M are calculatedTAnd fitting a functional relation graph of the starting resistance torque of the engine and the rotating speed of the engine.
6. The method of measuring aircraft engine starting drag torque under unloaded conditions of claim 5, wherein M is removed prior to step S4TOutlier points in the values.
7. The method for measuring the starting moment of drag of the aircraft engine under the unloaded condition of claim 1, wherein in the step S4, N is 80-120.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114136644A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Device and method for measuring resistance of air inlet channel in aircraft engine ground platform test |
| CN114935419A (en) * | 2022-05-19 | 2022-08-23 | 中国航发沈阳发动机研究所 | Method for evaluating power characteristics of aircraft engine starter under installation condition |
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| US20200003072A1 (en) * | 2018-06-28 | 2020-01-02 | Hamilton Sundstrand Corporation | Air turbine starter with turbine air exhaust outlet valve |
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Patent Citations (5)
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| CN106342205B (en) * | 2010-08-31 | 2013-12-11 | 中国兵器工业集团第七○研究所 | Engine start moment of resistance method of testing |
| CN107916997A (en) * | 2016-10-11 | 2018-04-17 | 和谐工业有限责任公司 | Integrated actuating device for aircraft |
| US20180266328A1 (en) * | 2017-03-17 | 2018-09-20 | Hamilton Sundstrand Corporation | Air turbine starter with automated variable inlet vanes |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136644A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Device and method for measuring resistance of air inlet channel in aircraft engine ground platform test |
| CN114136644B (en) * | 2021-10-20 | 2023-09-19 | 中国航发四川燃气涡轮研究院 | Aeroengine ground table test air inlet channel resistance measuring device and method |
| CN114935419A (en) * | 2022-05-19 | 2022-08-23 | 中国航发沈阳发动机研究所 | Method for evaluating power characteristics of aircraft engine starter under installation condition |
| CN114935419B (en) * | 2022-05-19 | 2023-09-22 | 中国航发沈阳发动机研究所 | Method for evaluating power characteristics of starter of aero-engine under installed condition |
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