CN111271179B - Power performance test method for ram air turbine - Google Patents
Power performance test method for ram air turbine Download PDFInfo
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- CN111271179B CN111271179B CN201811476836.3A CN201811476836A CN111271179B CN 111271179 B CN111271179 B CN 111271179B CN 201811476836 A CN201811476836 A CN 201811476836A CN 111271179 B CN111271179 B CN 111271179B
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000011056 performance test Methods 0.000 title claims abstract description 8
- 238000012360 testing method Methods 0.000 claims abstract description 9
- 238000012545 processing Methods 0.000 claims description 6
- 238000002474 experimental method Methods 0.000 claims description 2
- 239000000126 substance Substances 0.000 claims description 2
- 238000000605 extraction Methods 0.000 description 3
- 238000012795 verification Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000005283 ground state Effects 0.000 description 1
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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
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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
-
- 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
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Wind Motors (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the field of ram air turbine performance tests, and relates to a power performance test method of a ram air turbine. The method comprises the following steps: firstly, connecting a ram air turbine (1) with a rotating speed torquemeter (3) and a load device (4), and installing an emergency brake disc (2) on an output shaft at the rear end of the ram air turbine (1); step two, fixing the ram air turbine blade at the initial pitch angle theta1(ii) a Step three, starting the wind tunnel to stabilize the wind speed at the initial wind speed v1(ii) a Step four, slowly reducing the load to gradually increase the rotating speed of the ram air turbine; increasing the load to a state that the ram air turbine cannot rotate, and reducing the wind speed of the wind tunnel to 0 and shutting down the wind tunnel; step seven, increasing the pitch angle of the ram air turbine blade to theta2、θ3、θ4. The method is simple to operate and low in cost, and can be used for testing the power performance of the ram air turbine in the full flight envelope range in a ground low-speed wind tunnel.
Description
Technical Field
The invention belongs to the field of ram air turbine performance tests, and relates to a power performance test method of a ram air turbine.
Background
The ram air turbine system is an emergency energy source of the airplane, and when the airplane is in an emergency state, the energy of ram air can be absorbed and converted into emergency hydraulic energy or emergency electric energy.
The Ram Air Turbine (RAT) is an energy extraction component of a ram air turbine system, and is the most core component in the system, and the power extraction capability of the ram air turbine under each use condition directly determines the power provided by the system to an airplane in an emergency state. At present, the mainstream ram air turbines all have the following characteristics: 1. the size of the pitch angle of the turbine blade can be self-adjusted according to external working conditions; 2. the speed regulating mechanism is arranged in the turbine, and the rotating speed of the turbine can be stabilized near the rated rotating speed under all working conditions.
The ram air turbine system's envelope of use coincides with the aircraft flight envelope and should provide the ability to provide sufficient power at all flight altitudes, speeds. To meet this demand, ram air turbine power extraction performance in full-envelope conditions needs to be verified. The power performance conformance of the ram air turbine system generally needs to pass through air flight verification, however, a common low-speed wind tunnel cannot simulate high-altitude (corresponding to lower air density) and high-speed working conditions, and therefore, before air verification, if the power performance of a product cannot be found at ground state, air test and design requirements may be inconsistent, and high time and cost waste may be caused.
Disclosure of Invention
The purpose of the invention is as follows: by utilizing the principle of similarity of tip speed ratios, a test method for obtaining the power performance of the ram air turbine in the full flight envelope range in a ground low-speed wind tunnel is provided.
The technical scheme of the invention is as follows:
a method for testing the power performance of a ram air turbine, the method comprising the steps of:
firstly, connecting a ram air turbine 1 with a rotating speed torquemeter 3 and a load device 4, and installing an emergency brake disc 2 on an output shaft at the rear end of the ram air turbine 1;
secondly, fixing the blades of the ram air turbine 1 at the initial pitch angle theta1At the moment, the blades are ensured not to deflect under any working condition, so that the size of the load is ensured that the ram air turbine 1 cannot rotate under the maximum wind tunnel wind speed;
step three, starting the wind tunnel to stabilize the wind speed at the initial wind speed v1；
Step four, slowly reducing the load to gradually increase the rotating speed of the ram air turbine 1, and recording a group of rotating speed-torque curves at the wind speed in the process;
step five, increasing the load to the state that the ram air turbine 1 cannot rotate, and respectively increasing the wind speed to v2、v3、v4… …, repeating the step four;
step six, reducing the wind speed of the wind tunnel to 0, and shutting down the wind tunnel;
step seven, increasing the pitch angle theta of the blades of the ram air turbine 12、θ3、θ4… …, repeating the third step to the sixth step to ensure that the blades do not deflect under any working conditions and ensure that the ram air turbine 1 cannot rotate under the maximum wind tunnel wind speed due to the load;
step eight, according to the test steps, obtaining wind speed-torque curve clusters corresponding to different blade pitch angles, and carrying out dimensionless processing to obtain tip speed ratio-power coefficient curve clusters corresponding to different pitch angles theta;
and step nine, according to the curve cluster in the step eight, the dimensionless formula and the atmospheric data table, reversely checking the atmospheric density rho and the true speed V corresponding to all the working condition points on the flight envelope curve, and reversely deducing the power of the ram air turbine 1 under all the height and speed states on the full envelope curve.
Preferably, according to the principle of tip speed ratio similarity, a tip speed ratio-power coefficient curve cluster corresponding to different pitch angles θ is obtained through dimensionless processing, and the dimensionless processing formula is as follows:
λ＝Vblade tip/VWind power＝rtip·ω/VWind power＝Rtip·n·2π/(60·VWind power)；
P＝T·n；
λ -tip ratio;
Vblade tipLinear tip speed
VWind power-incoming flow wind speed
RtipThe distance of the blade tip from the turbine center, equal to the turbine radius
n-turbine speed
P-turbine power
T-turbine torque
CP-power factor
P-air Density
A is the area of the turbine propeller disc.
Preferably, the turbine power of the ram air turbine 1 under all working conditions of the full envelope is obtained by reverse-deducing from a tip speed ratio-power coefficient curve cluster and an atmospheric data table, wherein the reverse-deducing formula is as follows:
λ＝Vblade tip/VWind power＝rtip·ω/VWind power＝Rtip·n·2π/(60·VWind power)；
P＝T·n；
Preferably, in the experiment, if the turbine speed exceeds the rated speed due to an improper operation, the emergency brake disc 2 should be used immediately to reduce the ram air turbine 1 speed to zero.
Preferably, θ in step two1Theta in step seven for the initial pitch angle of the ram air turbine 12、θ3、θ4… … is the angle after feathering, relative to θ1Increasing, set maximum pitch angle θmaxThe maximum pitch angle that the turbine may exhibit over the full envelope.
The invention has the advantages that:
the invention provides a test method for obtaining ram air turbine power performance in a full flight envelope range in a ground low-speed wind tunnel. According to the principle of sharp speed ratio similarity, the power performance data of the ram air turbine at high altitude and high speed can be obtained in a conventional ground wind tunnel, and a full envelope power output value is obtained. The method can obtain more accurate high-altitude performance data at the initial design stage, reduces the risk of aerial verification, saves the test time and cost, and has better application prospect and economy.
Description of the drawings:
FIG. 1 is a schematic diagram of a test installation arrangement;
FIG. 2 is a typical cluster of tip speed ratio-power curves at different pitch angles.
Detailed Description
The invention is described in detail below with reference to the accompanying drawings. Please refer to fig. 1-2 of the specification.
The ram air turbine 1 is connected with a rotating speed torquemeter 3 and a load device 4, the load device can be a hydraulic pump, a generator or other load devices with adjustable sizes, and an emergency brake disc 2 is arranged on an output shaft at the rear end of the ram air turbine 1 and used for emergency braking when the rotating speed of the turbine is overlarge. The installation diagram is shown in figure 1.
Fixing ram air turbine blades at an initial pitch angle θ1(ensuring that the blades do not deflect under any working condition), the load is in a larger state, and the size of the load ensures that the ram air turbine cannot rotate under the maximum wind tunnel wind speed.
Starting the wind tunnel to stabilize the wind speed at the initial wind speed v1The wind speed can drive the turbine to rotate in an unloaded state.
The load is slowly reduced so that the ram air turbine speed is spun from zero and gradually increased, during which a set of speed-torque curves is recorded at this wind speed.
Increasing the load to a state where the ram air turbine cannot rotate, and increasing the wind speed to v2、v3、v4… …, repeating the step 4.
And reducing the wind speed of the wind tunnel to 0, and shutting down the wind tunnel.
And (3) increasing the pitch angles of the ram air turbine blades to theta 2, theta 3, theta 4 and … … (ensuring that the blades do not deflect under any working conditions), keeping the load in a larger state, ensuring that the ram air turbine cannot rotate under the maximum wind tunnel wind speed, and repeating the steps from 3 to 6.
And obtaining corresponding wind speed-torque curve clusters under different turbine pitch angles according to the test steps. According to the formula: λ ═ VBlade tip/VWind power＝rtip·ω/VWind power＝Rtip·n·2π/(60·VWind power)；P＝T·n；
Obtaining the tip speed ratio-work corresponding to different pitch angles theta through dimensionless processingThe coefficient curve cluster is extracted. A typical cluster of curves is shown in figure 2.
And (4) according to the curve cluster and the atmospheric data table in the step 8, reversely checking the atmospheric density rho and the true speed V corresponding to all the working condition points on the flight envelope curve, and reversely calculating the power of the turbine at all the heights and the speed states on the full envelope curve.
Claims (3)
1. A method for testing the power performance of a ram air turbine, the method comprising the steps of:
firstly, connecting a ram air turbine (1) with a rotating speed torquemeter (3) and a load device (4), and installing an emergency brake disc (2) on an output shaft at the rear end of the ram air turbine (1);
secondly, fixing the blades of the ram air turbine (1) at the initial pitch angle theta1At the moment, the blades are ensured not to deflect under any working condition, so that the size of the load is ensured that the ram air turbine (1) cannot rotate under the maximum wind tunnel wind speed;
step three, starting the wind tunnel to stabilize the wind speed at the initial wind speed v1；
Step four, slowly reducing the load to gradually increase the rotating speed of the ram air turbine (1), and recording a group of rotating speed-torque curves at the wind speed in the process;
increasing the load to the state that the ram air turbine (1) cannot rotate, and respectively increasing the wind speed to v2、v3、v4… …, repeating the step four;
sixthly, reducing the wind speed of the wind tunnel to 0, and shutting down the wind tunnel;
step seven, increasing the blade pitch angle of the ram air turbine (1) to theta2、θ3、θ4… …, ensuring that the blade does not deflect under any working condition, ensuring that the ram air turbine (1) cannot rotate under the maximum wind tunnel wind speed due to the load, and repeating the third step to the sixth step;
step eight, according to the test steps, obtaining wind speed-torque curve clusters corresponding to different blade pitch angles, and carrying out dimensionless processing to obtain tip speed ratio-power coefficient curve clusters corresponding to different pitch angles theta;
step nine, according to the step eight curve clusters, the dimensionless formula and the atmosphere data table, reversely checking the atmosphere density rho and the true speed V corresponding to all the working point positions on the flight envelope curve, and reversely deducing the power of the ram air turbine (1) under all the height and speed states on the full envelope curve;
according to the tip speed ratio similarity principle, obtaining tip speed ratio-power coefficient curve clusters corresponding to different pitch angles theta through dimensionless processing, wherein the dimensionless processing formula is as follows:
λ＝Vblade tip/VWind power＝rtip·ω/VWind power＝Rtip·n·2π/(60·VWind power)；
P＝T·n；
λ -tip ratio;
Vblade tipLinear tip speed
VWind (W)-incoming flow wind speed
RtipThe distance of the blade tip from the turbine center, equal to the turbine radius
n-turbine speed
P-turbine power
T-turbine torque
CP-power factor
P-air density
A-turbine paddle area;
the turbine power of the ram air turbine (1) under all working conditions of the full envelope curve is obtained by reverse thrust of a sharp speed ratio-power coefficient curve cluster and an atmospheric data table, and the reverse thrust formula is as follows:
λ＝Vblade tip/VWind (W)＝rtip·ω/VWind power＝Rtip·n·2π/(60·VWind power)；
P＝T·n；
2. A power performance test method of a ram air turbine (1) according to claim 1, characterized in that: in the experiment, if the turbine speed exceeds the rated speed due to misoperation, the emergency brake disc (2) should be used immediately to reduce the ram air turbine (1) speed to zero.
3. A power performance test method of a ram air turbine (1) according to claim 1, characterized in that: theta in step two1Theta in step seven for the ram air turbine (1) initial pitch angle2、θ3、θ4… … is the angle after feathering, relative to θ1Increasing, set maximum pitch angle θmaxThe maximum pitch angle that the turbine may exhibit over the full envelope.
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| CN201811476836.3A CN111271179B (en) | 2018-12-04 | 2018-12-04 | Power performance test method for ram air turbine |
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| CN201811476836.3A CN111271179B (en) | 2018-12-04 | 2018-12-04 | Power performance test method for ram air turbine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011150931A2 (en) * | 2010-06-02 | 2011-12-08 | Vestas Wind Systems A/S | A method for operating a wind turbine at improved power output |
| CN106194603A (en) * | 2016-08-31 | 2016-12-07 | 沈阳航空航天大学 | A kind of synchronism detection wind energy conversion system pneumatic efficiency and the device and method of generating efficiency |
| CN206054188U (en) * | 2016-08-31 | 2017-03-29 | 沈阳航空航天大学 | A kind of device of synchronism detection wind energy conversion system pneumatic efficiency and generating efficiency |
| WO2017092297A1 (en) * | 2015-12-02 | 2017-06-08 | 中国电力科学研究院 | Method for evaluating power characteristics of wind turbines, apparatus and storage medium |
| CN108036917A (en) * | 2017-12-15 | 2018-05-15 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of ram-air turbine wind tunnel test test method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7420289B2 (en) * | 2006-12-06 | 2008-09-02 | General Electric Company | Method for predicting a power curve for a wind turbine |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011150931A2 (en) * | 2010-06-02 | 2011-12-08 | Vestas Wind Systems A/S | A method for operating a wind turbine at improved power output |
| WO2017092297A1 (en) * | 2015-12-02 | 2017-06-08 | 中国电力科学研究院 | Method for evaluating power characteristics of wind turbines, apparatus and storage medium |
| CN106194603A (en) * | 2016-08-31 | 2016-12-07 | 沈阳航空航天大学 | A kind of synchronism detection wind energy conversion system pneumatic efficiency and the device and method of generating efficiency |
| CN206054188U (en) * | 2016-08-31 | 2017-03-29 | 沈阳航空航天大学 | A kind of device of synchronism detection wind energy conversion system pneumatic efficiency and generating efficiency |
| CN108036917A (en) * | 2017-12-15 | 2018-05-15 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of ram-air turbine wind tunnel test test method |
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