CN113447201B - Aeroengine rotational inertia measurement method under loading condition - Google Patents
Aeroengine rotational inertia measurement method under loading condition Download PDFInfo
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- 238000012360 testing method Methods 0.000 claims abstract description 34
- 230000005540 biological transmission Effects 0.000 claims abstract description 30
- 230000008569 process Effects 0.000 claims abstract description 23
- 238000005070 sampling Methods 0.000 claims description 4
- 230000004044 response Effects 0.000 claims description 3
- 238000005259 measurement Methods 0.000 description 5
- 238000004364 calculation method Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 4
- 239000010687 lubricating oil Substances 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
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Classifications
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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
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/10—Determining the moment of inertia
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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
Abstract
The application belongs to the technical field of engine tests, and particularly relates to a method for measuring rotational inertia of an aeroengine under loading conditions. The method comprises the following steps: 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 air source conditions in the starting process of the engine, and performing an engine starting test by utilizing the calibrated air source conditions; in the time period from the successful starting of the engine to the completion of the starting, different components are loaded according to time sequence, residual torque of a plurality of time nodes of the power transmission shaft is obtained, and the engine rotating speed of a plurality of corresponding time nodes is obtained; the engine moment of inertia is determined. According to the application, through measuring the rotational inertia of a plurality of time nodes in the starting process of the engine, the test data of the starting process of the engine can be more accurately obtained, and powerful test data support is provided for the type selection of the starter for the engine assembly.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a method for measuring rotational inertia of an aeroengine under loading conditions.
Background
Aircraft engines, which are among the most important devices of an aircraft, are able to provide the necessary thrust for the flight of the aircraft. The aero-engine is transited from a stationary state to a working state, the aero-engine needs to be rotated by a starter, and the output torque of the starter needs to overcome the influence of the rotation torque of the aero-engine to realize effective starting. For the ground test examination of an aircraft starting system, the examination of the capability of the starting system is generally required before the joint test with an engine, the rotational inertia of the engine directly influences the acceleration characteristic of the aircraft starting, and at present, the rotational inertia of the engine is difficult to accurately obtain, so that the examination of a starter is generally carried out together with the engine, the development risk of the aircraft starting system cannot be solved in advance, in the traditional model design process, the starting system is taken as an important examination item, and the starting system is specified in detail in GJBs 241A-2010, GJBs 2187A-2015 and HB 6630-92.
In the existing aircraft engine starting system design process, the output power of a starter is simulated mainly by a dynamometer mode, the starter belt forward engine starting acceleration process can only pass through a ground test mode, a relevant judging and simulating method is lacked, and the design of a relevant starting system is developed by combining engineering experience and test mode, so that the following difficulties and problems mainly exist:
1. because the aeroengine starting process is a complex dynamic process, the structural parameters of internal geometric components, friction force in the rotor rotating process, lubricating oil viscosity, oil-gas ratio of engine ignition, ignition energy, air supply conditions and the like have direct influence on the engine rotational inertia measurement, and how to accurately calibrate the rotational inertia of the engine so as to obtain the engine, starter and aircraft starting load characteristics is a complex engineering problem;
2. the traditional gas turbine starter is adopted to start an aeroengine, the starter can carry out performance index assessment before delivery, generally only whether the output power of the starter meets the standard or not can not be assessed, whether the starter can forward the engine to start in a unit time zone or not can not be assessed, mainly because the traditional starter standard test adopts a flywheel to simulate the rotational inertia of the engine, the error is larger, and the index assessment is influenced;
3. the moment of inertia in the traditional engine starting process is analyzed through parametric modeling, related assumptions are often needed in the modeling process, a complex dynamic physical process is characterized through a mathematical model, and the influence of cold and hot state gaps of a rotor, dynamic viscosity of lubricating oil, friction force of the rotor, fuel atomization efficiency and the like can cause larger calculation result deviation and cannot be accurately calculated;
4. in special environments such as plateau airports, the acquisition of the rotational inertia of an engine is critical to the evaluation of the starting capability of the aircraft, a large number of ground starting tests are often developed under the special environments to be bottomed, and the rotational inertia and other parameters of the engine under the special environments cannot be simulated to be evaluated under the conventional test environments, so that the cost of development period, research and development costs and the like are relatively high.
5. In the test of starting the aero-engine, a generator or a hydraulic pump is usually loaded at the same time, so that the load characteristic of the engine is considered when the moment of inertia of the aero-engine is measured, and the moment of inertia of the aero-engine is accurately obtained.
Disclosure of Invention
In order to solve the problems, the application provides a method for measuring the rotational inertia of an aeroengine under loading condition, which mainly comprises the following steps:
step S1, driving an air turbine starter to rotate through an air source control device, driving a gear shaft of an accessory transmission device to rotate through the air turbine starter, wherein the accessory transmission device is respectively connected with different load components and is connected with an engine transmission device through a power transmission shaft, so that the engine transmission device and each load component are driven to start and work according to a set time sequence, and a torque measuring device is arranged on the power transmission shaft;
s2, calibrating air source conditions in the starting process of the engine, and performing an engine starting test by utilizing the calibrated air source conditions;
step S3, in a period T from successful engine start to completion of start 0 In the T, the loading starting time T of different load components is recorded 1 ,T 2 …T n Will T 0 T is divided into (T) 0 ，T 1 )，(T 1 ，T 2 )...(T n T) different time periods, respectively obtaining the residual torque of a plurality of time nodes of the power transmission shaft and the engine rotating speed of the plurality of time nodes in each time period;
and S4, determining the rotational inertia of the engine as an average value of the rotational inertia of each time period.
Wherein, moment of inertia J in each time period P The method comprises the following steps:
wherein f (n i ) Residual torque of the ith time node of the corresponding time period; g (t) i ) And the engine speed of the ith time node of the corresponding time period is set as N, and the number of the time nodes of the corresponding time period is set as N.
Preferably, in step S2, an engine start control plan and timing are acquired, and an engine start test is performed in accordance with the engine start control plan and timing.
Preferably, in step S2, the air supply conditions for calibrating the engine starting process include calibrating ambient pressure, ambient temperature, air supply device pressure, air supply device temperature, air turbine starter efficiency, air line control valve response.
Preferably, step S3 further includes:
step S31, a plurality of residual torques acquired by the torque measuring device according to sampling frequency are acquired;
step S32, obtaining a first relation curve n=g (t) of the engine speed changing with time;
step S33, fitting a second relation curve m=f (n) of the residual torque and the rotational speed;
step S34, discretizing the engine speeds of the s×n time nodes on the first relationship curve, discretizing the residual torques of the s×n time nodes on the second relationship curve, and each time period is N time nodes.
Preferably, before step S33, further comprising removing outliers in the collected plurality of residual torques.
Preferably, in step S3, N has a value of 30 to 50.
Preferably, in step S4: t (T) 0 The value is 0, and the load components are a generator and a hydraulic press. Recording the starting loading time T of the generator in the period from the success of starting the engine to the completion of starting 1 Time T for starting loading of hydraulic press 2 Respectively obtaining the residual torque of N time nodes of different time periods of the power transmission shaft and the engine rotating speed of the N time nodes of the time period; determining the rotational inertia of the engine as the engine starting to finishing process:
J＝(J 1 +J 2 +J 3 )/3
wherein the method comprises the steps of
Wherein t is 11 ,t 12 ,…,t 1N ∈(0,T 1 )，
Wherein t is 21 ,t 22 ,…,t 2N ∈(T 1 ,T 2 )，
Wherein t is 31 ,t 32 ,…,t 3N ∈(T 2 ,t)，
The rotational inertia of the engine is directly measured through a test, the output torque characteristic of the air turbine starter mainly converts the energy of air into mechanical shaft power, the measurement accuracy is high, the air turbine starter is not required to be supplied with oil and controlled, 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 realize, and the real engine rotational inertia result can be obtained.
According to the application, through measuring the rotational inertia of a plurality of time nodes in different loads and different time sequences in the engine starting process, the test data in the engine starting process can be more accurately obtained, and powerful test data support is provided for the type selection of the starter for engine assembly.
Drawings
FIG. 1 is a flow chart of a method of measuring the moment of inertia of an aircraft engine under loading conditions of the present application.
FIG. 2 is a flow chart of an engine moment of inertia measurement test.
FIG. 3 is a schematic illustration of an engine moment of inertia measurement test environment.
FIG. 4 is a schematic diagram of engine residual torque versus engine speed.
FIG. 5 is a schematic diagram of engine speed versus time.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail 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 application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, based on the embodiments of the application, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides a method for measuring rotational inertia of an aeroengine under loading condition, which mainly comprises the following steps as shown in figure 1:
step S1, driving an air turbine starter to rotate through an air source control device, driving a gear shaft of an accessory transmission device to rotate through the air turbine starter, wherein the accessory transmission device is respectively connected with different load components and is connected with an engine transmission device through a power transmission shaft, so that the engine transmission device and each load component are driven to start and work according to a set time sequence, and a torque measuring device is arranged on the power transmission shaft;
and S2, calibrating air source conditions in the starting process of the engine, and performing an engine starting test by utilizing the calibrated air source conditions.
Step S3, in a period T from successful engine start to completion of start 0 In the T, the loading starting time T of different load components is recorded 1 ,T 2 ...T n Will T 0 T is divided into (T) 0 ，T 1 )，(T 1 ，T 2 )...(T n T) different time periods, respectively obtaining the residual torque of a plurality of time nodes of the power transmission shaft and the engine rotating speed of the plurality of time nodes in each time period;
and S4, determining the rotational inertia of the engine as an average value of the rotational inertia of each time period.
Wherein, moment of inertia J in each time period P The method comprises the following steps:
wherein f (n i ) Residual torque of the ith time node of the corresponding time period; g (t) i ) And the engine speed of the ith time node of the corresponding time period is set as N, and the number of the time nodes of the corresponding time period is set as N.
The first step: calibration of engine starting reference
And calibrating the test environment and the state of the rotational inertia of the aero-engine. The system specifically comprises ambient pressure, ambient temperature, pressure of air source equipment, temperature of the air source equipment, efficiency of an air turbine starter, efficiency of an air pipeline, response condition of an air pipeline control valve, and working states of a generator and a hydraulic pump.
And a second step of: test for starting engine
The method comprises the steps of performing an engine starting test by using calibrated air source conditions and test equipment, adjusting air source parameters by using a data test system, giving a control plan of an air pipeline control valve, starting according to a starting control plan and time sequence of an engine, adjusting the opening rate of the control valve according to the starting process of the engine, converting air pressure power of air into mechanical shaft power by an air turbine starter, outputting the mechanical shaft power, driving a gear shaft in an accessory transmission device to rotate by using the gear shaft, transmitting the shaft power to the engine transmission device by using the power transmission shaft, driving an engine rotor part to rotate by using the gear shaft, enabling the engine to enter a starting state, and respectively starting loading (working) by using a generator and a hydraulic pump according to the control plan. If the engine is not started successfully, the air source parameter is adjusted until the engine is started successfully.
And a third step of: data recording
When the engine is successfully started, the total residual torque value M at different rotating speeds in the starting process of the engine is obtained by a torque measuring device arranged on a power transmission shaft, the change curve of the rotating speed n of the engine along with the time T is recorded, and the starting loading time T of a generator is recorded 1 And the hydraulic pump start loading time T 2 Restoring to the initial state before starting until starting is completed, and obtaining the starting characteristic of the engine;
fourth step: performing data processing
In the engine starting test link, the total residual torque of the air turbine starter with the starter starting by the engine is obtained by a torque measuring device arranged on a power transmission shaft
Wherein M is total residual torque of engine starting, n is engine speed, t is time, and J is rotational inertia of an engine rotor.
From the first step, a profile m=f (n) of the total remaining torque M of the engine start with the rotational speed n and a profile n=g (t) of the rotational speed n of the engine with the time t are obtained.
In some alternative embodiments, the starting time point of the whole starting process is taken to be 0, the load components are a generator and a hydraulic machine, and N points are taken for each time period.
At a time of 0 to T 1 Stage t 11 ,t 12 ,…,t 1N ∈(0,T 1 )，
……
Then there are:
at time T 1 ～T 2 Stage t 21 ,t 22 ,…,t 2N ∈(T 1 ,T 2 )，
……
Then there are:
at time T 2 Stage t, t 31 ,t 32 ,…,t 3N ∈(T 2 ,t)，
……
Then there are:
therefore, the engine moment of inertia
J＝(J 1 +J 2 +J 3 )/3。
In some alternative embodiments, step S3 further comprises:
step S31, a plurality of residual torques acquired by the torque measuring device according to sampling frequency are acquired;
step S32, obtaining a first relation curve n=g (t) of the engine speed changing with time;
step S33, fitting a second relation curve m=f (n) of the residual torque and the rotational speed;
and step S34, discretizing the engine speeds of the 3N time nodes on the first relation curve, and discretizing the residual torques of the 3N time nodes on the second relation curve.
It can be understood that the method samples a plurality of data, and is more beneficial to the processing and processing of later-stage data through a smooth curve fitted by the curve, and in step S34, a plurality of time nodes conforming to the actual situation can be further discretized according to the need through different discrete equations, so as to provide more accurate test data for the subsequent moment of inertia calculation.
In some alternative embodiments, prior to step S33, further comprising removing outlier points in the collected plurality of residual torques. It is well known to those skilled in the art that outlier points are points where the gradient of the change in the sampled value cannot be achieved within one sampling period in an actual system. The fitted curve is more in line with the actual situation by removing the outlier points.
In some alternative embodiments, in step S3, N has a value of 30 to 50. It can be understood by those skilled in the art that the change slope of the torque has a larger influence on the result according to the torque calculation formula, and the slope of the change curve of the torque with the rotation speed in the engine starting process continuously changes according to fig. 4 and 5.
The traditional gas turbine starter is adopted to start an aeroengine, the starter can carry out performance index assessment before delivery, generally only whether the output power of the starter meets the standard or not can not be assessed, whether the starter can forward the engine to start in a unit time zone or not can not be assessed, mainly because the traditional starter standard test adopts a flywheel to simulate the rotational inertia of the engine, the error is larger, and the index assessment is influenced; the moment of inertia is analyzed through parameterized modeling, related assumptions are needed in the modeling process, a complex dynamic physical process is characterized through a mathematical model, and the influence of cold and hot state gaps of a rotor, dynamic viscosity of lubricating oil, friction force of the rotor, fuel atomization efficiency and the like can cause larger deviation of a calculation result and cannot be accurately calculated and given.
By adopting the method, the rotational inertia of the engine is directly measured through a test. The output torque characteristic of the air turbine starter is mainly that energy of air is converted into mechanical shaft power, measurement accuracy is high, oil supply and control are not needed for the air turbine starter, the exhaust gas temperature of the air turbine starter is far lower than the exhaust gas emission temperature of the gas turbine starter, test operation is simple and convenient to achieve, and a real engine rotational inertia result can be obtained.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The method for measuring the rotational inertia of the aeroengine under the loading condition is characterized by comprising the following steps of:
step S1, driving an air turbine starter to rotate through an air source control device, driving a gear shaft of an accessory transmission device to rotate through the air turbine starter, wherein the accessory transmission device is respectively connected with different load components and is connected with an engine transmission device through a power transmission shaft, so that the engine transmission device and each load component are driven to start and work according to a set time sequence, and a torque measuring device is arranged on the power transmission shaft;
s2, calibrating air source conditions in the starting process of the engine, and performing an engine starting test by utilizing the calibrated air source conditions;
step S3, in a period T from successful engine start to completion of start 0 In the T, the loading starting time T of different load components is recorded 1 ,T 2 ...T n Will T 0 T is divided into (T) 0 ，T 1 )，(T 1 ，T 2 )...(T n T) different time periods, respectively obtaining the residual torque of a plurality of time nodes of the power transmission shaft and the engine rotating speed of the plurality of time nodes in each time period;
step S4, determining the rotational inertia of the engine as an average value of the rotational inertia of each time period,
wherein, moment of inertia J in each time period P The method comprises the following steps:
wherein f (n i ) At the ith time of the corresponding time periodResidual torque of the intermediate node; g (t) i ) And the engine speed of the ith time node of the corresponding time period is set as N, and the number of the time nodes of the corresponding time period is set as N.
2. The method for measuring the moment of inertia of an aircraft engine under loading according to claim 1, wherein 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.
3. The method for measuring rotational inertia of an aircraft engine under loading conditions according to claim 2, wherein in step S2, the air supply conditions for calibrating the engine starting process include calibrating ambient pressure, ambient temperature, air supply equipment pressure, air supply equipment temperature, air turbine starter efficiency, air line control valve response.
4. The method for measuring the moment of inertia of an aircraft engine under loading conditions according to claim 1, wherein step S3 further comprises:
step S31, a plurality of residual torques acquired by the torque measuring device according to sampling frequency are acquired;
step S32, obtaining a first relation curve n=g (t) of the engine speed changing with time;
step S33, fitting a second relation curve m=f (n) of the residual torque and the rotational speed;
step S34, discretizing the engine speeds of s×n time nodes on the first relationship curve, discretizing the residual torques of s×n time nodes on the second relationship curve, where S is a time period, and each time period includes N time nodes.
5. The method for measuring rotational inertia of an aircraft engine under loading conditions of claim 4, further comprising removing outlier points in the collected plurality of residual torques prior to step S33.
6. The method for measuring the rotational inertia of an aircraft engine under loading conditions according to claim 1, wherein in the step S3, the value of N is 30 to 50.
7. The method for measuring the moment of inertia of an aircraft engine under loading conditions according to claim 4, wherein in step S4: t (T) 0 The value is 0, the load components are a generator and a hydraulic press, and the loading starting time T of the generator is recorded in the period from the successful starting of the engine to the completion of the starting 1 Time T for starting loading of hydraulic press 2 Respectively obtaining the residual torque of N time nodes of different time periods of the power transmission shaft and the engine rotating speed of N time nodes of corresponding time periods;
the engine rotational inertia is determined as:
J＝(J 1 +J 2 +J 3 )/3
wherein the method comprises the steps of
Wherein t is 11 ,t 12 ,…,t 1N ∈(0,T 1 )，
Wherein t is 21 ,t 22 ,…,t 2N ∈(T 1 ,T 2 )，
Wherein t is 31 ,t 32 ,…,t 3N ∈(T 2 ,t)。
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0162398A1 (en) * | 1984-05-18 | 1985-11-27 | Siemens Aktiengesellschaft | Process and device for determining the torque of a torque generator |
| EP0704689A2 (en) * | 1994-09-30 | 1996-04-03 | AVL Gesellschaft für Verbrennungskraftmaschinen und Messtechnik mbH.Prof.Dr.Dr.h.c. Hans List | Procedure for determining the moment of inertia |
| KR19990052042A (en) * | 1997-12-20 | 1999-07-05 | 정몽규 | How to measure the moment of rotational inertia of an engine |
| CN201803831U (en) * | 2010-08-25 | 2011-04-20 | 襄樊达安汽车检测中心 | Device for measuring inertia moment parameters of automobile engine assembly |
| CN102374924A (en) * | 2010-08-23 | 2012-03-14 | 中国航空工业集团公司航空动力控制系统研究所 | Measurement method of moment of inertia of separately excited DC (Direct Current) motor |
| RU2581891C1 (en) * | 2015-02-24 | 2016-04-20 | Общество с ограниченной ответственностью "Научно-исследовательский институт "Мехмаш" | Method of determining reduced moment of inertia of pre-transformer zone of hydromechanical transmission of vehicle |
| CN107782498A (en) * | 2017-10-10 | 2018-03-09 | 中国石油集团川庆钻探工程有限公司 | Measure the system and method for diesel engine equivalent rotary inertia |
| CN112213106A (en) * | 2020-10-16 | 2021-01-12 | 中国直升机设计研究所 | Helicopter APU starting load simulation system |
-
2021
- 2021-06-01 CN CN202110609826.8A patent/CN113447201B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0162398A1 (en) * | 1984-05-18 | 1985-11-27 | Siemens Aktiengesellschaft | Process and device for determining the torque of a torque generator |
| EP0704689A2 (en) * | 1994-09-30 | 1996-04-03 | AVL Gesellschaft für Verbrennungskraftmaschinen und Messtechnik mbH.Prof.Dr.Dr.h.c. Hans List | Procedure for determining the moment of inertia |
| KR19990052042A (en) * | 1997-12-20 | 1999-07-05 | 정몽규 | How to measure the moment of rotational inertia of an engine |
| CN102374924A (en) * | 2010-08-23 | 2012-03-14 | 中国航空工业集团公司航空动力控制系统研究所 | Measurement method of moment of inertia of separately excited DC (Direct Current) motor |
| CN201803831U (en) * | 2010-08-25 | 2011-04-20 | 襄樊达安汽车检测中心 | Device for measuring inertia moment parameters of automobile engine assembly |
| RU2581891C1 (en) * | 2015-02-24 | 2016-04-20 | Общество с ограниченной ответственностью "Научно-исследовательский институт "Мехмаш" | Method of determining reduced moment of inertia of pre-transformer zone of hydromechanical transmission of vehicle |
| CN107782498A (en) * | 2017-10-10 | 2018-03-09 | 中国石油集团川庆钻探工程有限公司 | Measure the system and method for diesel engine equivalent rotary inertia |
| CN112213106A (en) * | 2020-10-16 | 2021-01-12 | 中国直升机设计研究所 | Helicopter APU starting load simulation system |
Non-Patent Citations (1)
| Title |
|---|
| 基于扭矩特性的航空发动机起动系统数学模型;苏伟生;航空动力学报;第20卷(第3期);第499-502页 * |
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