CN109668739A - A kind of test platform for more duct turbine nozzle Study on Integration - Google Patents
A kind of test platform for more duct turbine nozzle Study on Integration Download PDFInfo
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- CN109668739A CN109668739A CN201910030426.4A CN201910030426A CN109668739A CN 109668739 A CN109668739 A CN 109668739A CN 201910030426 A CN201910030426 A CN 201910030426A CN 109668739 A CN109668739 A CN 109668739A
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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 invention discloses a kind of test platforms for more duct turbine nozzle Study on Integration, including air inlet section, turbine section, outer culvert and third duct gas handling system and nozzle section, and turbine, jet pipe and inside and outside culvert blending problem are carried out Study on Integration；Electric heater is set before air inlet volute, guarantees mainstream and outer culvert fluid total temperature difference≤300K；More preferably to simulate the inside and outside blending contained between air-flow, turbine section outlet setting lobe injector；Outer culvert import is located at injector top, nozzle inlet, and nozzle inlet has the straight blending section such as close；Third duct is located at nozzle throat and outlet is intermediate, and outer culvert and third duct inlet -duct area are adjustable, realizes that bypass ratio changes within the scope of 0-1.0.The present invention is directed to more duct adaptive engine turbine nozzle design features, it is proposed more duct turbine nozzle integration experimental study platform structure frames, it influences each other and matching relationship to study turbine nozzle in more duct engines, grasps that jet pipe under more ducts is pneumatic and Stealth Fighter.
Description
Technical field
The present invention relates to a kind of test platforms for more duct turbine nozzle Study on Integration, belong to turbomachine technology
Field.
Background technique
Engine (Adaptive Cycle Engine, ACE) adaptively (is recycled) according to aircraft different task demand, is led to
It crosses and changes multiple adjustable geometry mechanism positions, using adaptive control technology, change fan, core engine flow and pressure ratio automatically,
So that engine is obtained optimal performance under friction speed and height in envelope curve, and reach most preferably with the composite behaviour of aircraft, is
Advanced variable cycle engine.With good combination property, oil consumption rate in envelope curve, low and aircraft range is long due to it, charge flow rate from
Dynamic matching, fly/hair composite behaviour is good, Stealth Fighter is good and is conducive to heat management the advantages such as designs, obtain World Airways engine
The great attention of advanced country.But due to its there are more than operation mode and state conversion is complicated, more than tunable component and mechanism is multiple
The technological difficulties such as miscellaneous and adjustable range is wide, regulated variable is more, it is difficult to study.2012 to 2016, United States Air Force tissue
About 6.85 hundred million dollars of investment carries out AETD plan, it is therefore an objective to promote using the adaptive of 3 flow passage structures on ADVENT Research foundation
The maturation of engine technology is answered, provides power for a variety of optimal in structures such as United States Air Force New-Generation Fighter or bomber.2016
On June 30, in, it is contemplated that 10 years by a definite date, United States Air Force put into 2,000,000,000 dollars of funds, carried out AETP project, by GE and PW company
Undertake technological development and verifying.AETP plan continues out the adaptive circulation basic feasible solution verified along ATED project
Work is opened up, realizes 3 runner adaptive engine smoothly transitting from technology prototype to engineering verification machine, target is: comparing mesh
Preceding technical level, engine fuel efficiency improve 25%, and thrust increases 10%, and tactical range extends 30%.
For traditional turbofan aero-engine, 3 flow passage structures can provide the air-flow of 1 strand of relative low temperature for believing
Number management, this means that extra air can be used in cooling hot-end component to reduce infrared signal, or enter core engine and plus
Power combustion chamber increases thrust.Since structure is complicated, manufacture difficulty is big, studies in China scholar is mostly individually from variable-geometry jet pipe
It sets out, it is assumed that uniformly, by adjustable jet tube throat area and molded line, test and the control of numerical simulation jet pipe are advised for nozzle inlet blending
Rule.But there are eddy flows for turbine outlet, and there are very strong blending with outer culvert air-flow, and turbine/jet pipe Study on Integration is being improved
While turbine performance, increases inside and outside culvert blending, shorten jet pipe length and simultaneously promote its stealth effect.In particular for 3 runner knots
Structure, it is necessary to consider that outer air-flow of containing influences nozzle performance.
Therefore, this invention proposes a kind of more duct turbine nozzle integration experimental study platforms, for next-generation adaptive
Engine is answered, turbine outlet eddy flow and outer culvert blending, third duct air-flow are comprehensively considered into efficient, the good exhaust system of Stealth Fighter
In system design and research.
Summary of the invention
Goal of the invention: in order to study aerodynamics problem present in next-generation adaptive more duct engine exhaust systems, this
Invention proposes a kind of test platform for more duct turbine nozzle Study on Integration, to study inside and outside culvert blending, bypass ratio
Exhaust system Rule adjusting within the scope of 0-1.0 is unfolded to further investigate, grind for adaptive engine to aerodynamics problem therein
Offer technology processed and test support.
Technical solution: to achieve the above object, the technical solution adopted by the present invention are as follows:
A kind of test platform for more duct turbine nozzle Study on Integration, including with flowering structure:
Air inlet section: the air inlet of air inlet volute is connected by electric heater with high-pressure air source, by electric heater to mainstream
It is heated, guarantees mainstream and the outer total temperature difference≤300K for containing air-flow, mainstream gas is transported to whirlpool by air inlet volute after heating
Take turns section；
Turbine section: including entry guide vane, rotor, exit guide blade and center cone, and turbine section exit is provided with injector,
For increasing the blending between outer culvert air-flow and turbine outlet mainstream gas, mainstream gas is transported to nozzle section by injector；
Outer culvert and third bypass air system, nozzle section: by-pass air duct import is set at the nozzle inlet above injector,
Straight blending section, the third duct import such as close is provided at nozzle inlet to be set between nozzle throat and nozzle exit；Outside
The area of duct import and third duct import is adjustable, guarantees total bypass ratio range 0-1.0.
The present invention combines 3 runner adaptive engine design features, and air inlet section, turbine section, outer culvert and third duct is empty
Gas system, nozzle section combine architectonical, mainstream is heated by electric heater, guarantee mainstream and outer culvert total airflow temperature it is poor≤
300K；Outer culvert and third duct discharge area are adjustable, meet Research Requirements within the scope of bypass ratio 0-1.0.
Further, the air inlet section, outer culvert and third bypass air system use same high-pressure air source, air inlet point
Do not connected by high pressure flow control valve with high-pressure air source valve.
Further, the wheel hub ratio of the turbine section is 0.65, and the ratio of turbine section axial length and nozzle section is 1:5.
It further, is the inside and outside blending contained between air-flow of more preferable simulation, the injector uses wave-pieced type injector, and wave
The axial length of flap-type injector is the 35% of turbine section.
Further, the third duct import is between nozzle throat and nozzle exit at the position 30-50%.
Further, the by-pass air duct import and the import of third duct control entrance width by control valve respectively, into
And realize the separately adjustable of by-pass air duct import and third duct inlet flow rate, guarantee total bypass ratio range 0-1.0.
Further, the entrance width adjustable range d of the by-pass air duct importw1=0~25mm, third duct import into
Mouth width degree adjustable range dw2=0~20mm.
The utility model has the advantages that a kind of test platform for more duct turbine nozzle Study on Integration provided by the invention, relatively
In the prior art, has the advantage that 1, turbine outlet eddy flow, inside and outside culvert blending, third duct air-flow are considered into exhaust system
In system, structure is relatively easy, has good master control effect；2, outer culvert and third duct flow realize individually control, the test
Platform under different outer culverts and third duct distribution ratio of liquid flow, can grind exhaust system development within the scope of total bypass ratio 0-1.0
Study carefully；3, injector, the inside and outside influence for containing blending to nozzle performance of analog are set at turbine outlet.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the embodiment of the present invention；
Fig. 2 is laboratory structure schematic diagram in the embodiment of the present invention；
Fig. 3 is the perspective view of turbine part in the embodiment of the present invention；
Fig. 4 is the perspective view of wave-pieced type injector in the embodiment of the present invention；
Fig. 5 is the perspective view of nozzle section in the embodiment of the present invention, by-pass air duct import and third duct import；
It include: 1, high-pressure air source, 2, high-pressure air source valve, 3, high pressure flow control valve, 4, electric heater, 5, air inlet in figure
Volute, 6, entry guide vane, 7, rotor, 8, rotor shaft, 9, exit guide blade, 10, center cone, 11, injector, 12, by-pass air duct
Import, 13, third duct import, 14, nozzle throat, 15, blending section, 16, control valve, 17, exhaust muffling device, 18, whirlpool
Flow dynamometer machine, 19, flow field survey equipment, 20, master control room.
Specific embodiment
The present invention will be further explained with reference to the accompanying drawings and embodiments.
It is as shown in Figure 1 a kind of test platform for more duct turbine nozzle Study on Integration, specifically includes that
Air inlet section: the air inlet of air inlet volute 5 is connected by electric heater 4 with high-pressure air source 1, right by electric heater 4
Mainstream is heated, and guarantees mainstream and the outer total temperature difference≤300K for containing air-flow, for studying under the different temperature difference to blending procedure
It influences, mainstream gas is transported to turbine section by air inlet volute 5 after heating；
Turbine section: including entry guide vane 6, rotor 7, exit guide blade 9 and center cone 10, and turbine section exit is provided with and draws
Emitter 11, for increasing the blending between outer culvert air-flow and turbine outlet mainstream gas, mainstream gas is transported to by injector 11
Nozzle section 14；
Outer culvert and third bypass air system, nozzle section 14: by-pass air duct import 12 is set to the jet pipe of 11 top of injector
14 entrances of section, 14 entrance of nozzle section are provided with straight blending section 15, the third duct import 13 such as close and are set to jet pipe larynx
Between road and nozzle exit；It is wide that the by-pass air duct import 12 and third duct import 13 control import by control valve 16 respectively
Degree, and then realize the separately adjustable of by-pass air duct import 12 and 13 flow of third duct import, guarantee total bypass ratio range 0-1.0.
In view of structure size and test demand, turbine section use 1.5 grades of turbines (as shown in Figure 3), including entry guide vane,
Rotor, exit guide blade and center cone blend section flow field structure and its to the influence of nozzle section to study under import eddy flow.It is preferred that
Design: turbine inlet flow 5kg/s, revolving speed 3000rpm, blow down ratio 1.35；Turbine part is carried out using three rank Bezier curves
Design preferentially determines entry guide vane outer diameter DS=0.4m, internal diameter DhThe parameters such as=0.26m, entry guide vane, rotor and outlet supporting plate
The number of blade is respectively 24,39 and 7, and exit guide blade is the load-carrying member of rotor.Center cone can select blunt according to different research objects
Short centrum or the long centrum of tip.
Turbine section outlet setting injector, it is approximate for increasing the blending between outer culvert air-flow and turbine outlet mainstream gas
The inside and outside culvert blending in actual engine is simulated, the geometric configuration of injector has circular platform type, tab, lobe type etc..Such as Fig. 4 institute
Show, to contain the blending between air-flow inside and outside more preferable simulation, injector uses wave-pieced type injector in the present embodiment, by 12 " lobes "
It is uniformly distributed one week, each " lobe " is by two sections of circular arcs and two sections of rectilinear(-al)s.
As shown in figure 5, containing outlet outside is located at air inlet section outlet, nozzle inlet, nozzle inlet has the straight blending section such as close,
To the inside and outside blending for containing air-flow, exit width adjustable range dw1=0~25mm；Third duct is located in nozzle throat and outlet
Between, about 50% position, exit width adjustable range dw2=0~20mm；Air inlet section, outer culvert and third bypass air system are using same
One high-pressure air source can heat mainstream according to the needs of practical problem, simulate inside and outside culvert gas flow temperature under true environment
Difference.
In the present embodiment, the wheel hub ratio of the turbine section is 0.65, and turbine section axial length and the ratio of nozzle section 14 are
1:5, the axial length of wave-pieced type injector are the 35% of turbine section.
The present invention is directed to the aerodynamics problem of turbine and jet pipe under more ducts, propose integrated experimental study platform, it can be achieved that
Bypass ratio changes within the scope of 0-1.0, has clear in structure, the goal in research outstanding features such as clearly.
Under conditions of high-pressure air source total flow 10kg/s, more duct turbines/jet pipe integration test platform is designed, is full
Sufficient bypass ratio variation range is set as 5kg/s in 0-1.0, by turbine section inlet design point flow, complete using three rank Beizer curves
It is designed at turbine section, and successively designs outlet injector, outer culvert and third duct, nozzle section according to turbine part size, determined
The specific structure size of the integration test platform.
More duct turbines/jet pipe integration laboratory arragement construction is as shown in Fig. 2, for the reliable of guarantee test measurement
Property, rotor shaft 8 is connected with eddy current dynamometer 18 guarantees that turbine stablizes output power, and nozzle exit connects exhaust noise silencing dress
17 reductions outlet noise is set, flow field survey equipment 19 can be selected by test measurement specific requirements, rotor speed, flow valve
Control and data processing carry out in master control room 20, and specific test procedure is as follows:
1. ensuring that the leakproofness such as reliable more duct turbines/jet pipe integrated test stand connection, pipeline and valve touch the mark
It is required that high pressure gas holder 1 is checked, if 1 pressure of high pressure gas holder opens high-pressure air source valve 2 in OK range；
2. connecting electric heater 4 and 18 power supply of eddy current dynamometer, the flow control valve 3 of main duct is opened, automatic adjustment should
Control valve 3 makes winner's duct flow be about 5kg/s；
3. stepping up 8 revolving speed of 4 power of electric heater and rotor shaft, high pressure draught total temperature improves about 100K~300K
(avoiding turbine inlet temperature (TIT) excessively high, to cause turbine output rate beyond eddy current dynamometer maximum power), the rotation of rotor shaft
Rotary speed improves and is maintained at rated speed 3000rpm；
4. when main duct stability of flow is in 5kg/s (± 0.2kg/s), 4 stable output power (500kw of electric heater capacity
~1500kw, is determined by experimental condition), rotor speed be rated speed 3000rpm, using the record of flow field survey equipment 19 without outer
Contain under airflow influence, turbine section and nozzle section flow field data, including turbine section and nozzle section import and export total temperature, stagnation pressure, flow angle
Etc. parameters；
5. keeping main duct flow basicly stable, open the flow total valve 3 of inlet channel, open and adjust by-pass air duct into
Mouthfuls 12 control valve 16 steps up outer 12 0~3kg/s of flow of culverts import, and keep it is outer contain flow it is constant be 3kg/s (±
0.2kg/s), outer culvert flow dynamics change procedure about 3min records dynamic and pulsatile flow field data using flow field survey equipment 19；
6. keeping main duct and outer culvert flow basicly stable, the control valve 16 of third duct import 13 is opened and adjusts,
13 0~2kg/s of flow of third duct import is stepped up, and keeping third duct flow constant is 2kg/s (± 0.1kg/s),
Third duct flow dynamics change procedure about 3min records dynamic and pulsatile flow field data using flow field survey equipment 19；
7. the more duct turbines of single/jet pipe integration test process is about 20min, flow field DATA REASONING process is about
15min successively closes outer contain and the control valve 16 of third duct, inlet channel flow total valve 3, electricity after the completion of test measurement
4 power supply of heater, main duct flow valve 3,18 power supply of eddy current dynamometer, high-pressure air source valve 2 terminate the more duct whirlpools of single
Wheel/jet pipe integration test.
The above is only a preferred embodiment of the present invention, it should be pointed out that: for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (7)
1. a kind of test platform for more duct turbine nozzle Study on Integration characterized by comprising
Air inlet section: including air inlet volute (5), electric heater (4), high-pressure air source (1), the air inlet of air inlet volute (5) passes through electricity
Heater (4) connects with high-pressure air source (1), for being heated to mainstream, guarantee mainstream and the outer total temperature difference for containing air-flow≤
300K, mainstream gas is transported to turbine section by air inlet volute (5) after heating；
Turbine section: including entry guide vane (6), rotor (7), exit guide blade (9) and center cone (10), and turbine section exit is arranged
There are injector (11), for increasing the blending between outer culvert air-flow and turbine outlet mainstream gas, mainstream gas passes through injector
(11) it is transported to nozzle section；
Nozzle section: it including nozzle inlet, the nozzle throat (14), nozzle exit being sequentially communicated, and is provided at nozzle inlet
Straight blending section (15)；
Outer culvert and third bypass air system: including being arranged in the by-pass air duct import (12) of nozzle inlet side-walls and being set to
The third duct import (13) of side-walls between nozzle throat (14) and nozzle exit, and by-pass air duct import (12) and third duct
The area of import (13) is adjustable, guarantees total bypass ratio range 0-1.0.
2. a kind of test platform for more duct turbine nozzle Study on Integration according to claim 1, feature exist
In the by-pass air duct import (12) and third duct import (13) are communicated with inlet channel jointly, and high-pressure air source (1) passes through
High pressure flow control valve (3) is connected to electric heater (4), inlet channel respectively；The by-pass air duct import (12) and third duct
It is respectively arranged with control valve (16) at import (13), realizes by-pass air duct import (12) and third duct by control valve (16)
Import (13) flow it is separately adjustable.
3. a kind of test platform for more duct turbine nozzle Study on Integration according to claim 1, feature exist
In the wheel hub ratio of the turbine section is 0.65, and the ratio of turbine section axial length and nozzle section is 1:5.
4. a kind of test platform for more duct turbine nozzle Study on Integration according to claim 1, feature exist
In the injector (11) uses wave-pieced type injector, and the axial length of wave-pieced type injector is the 35% of turbine section.
5. a kind of test platform for more duct turbine nozzle Study on Integration according to claim 1, feature exist
In the third duct import (13) is located between nozzle throat (14) and nozzle exit at the position 30-50%.
6. a kind of test platform for more duct turbine nozzle Study on Integration according to claim 1, feature exist
In the entrance width adjustable range d of the by-pass air duct import (12)w1=0~25mm, the entrance width of third duct import (13)
Adjustable range dw2=0~20mm.
7. a kind of test platform for more duct turbine nozzle Study on Integration according to claim 2, feature exist
In further including that connect with rotor shaft (8) eddy current dynamometer (18), the exhaust muffling device that connects with nozzle exit
(17), the flow field survey equipment (19) and master control room (20) being arranged in nozzle section and turbine section, and master control room (20) with
High pressure flow control valve (3), electric heater (4), control valve (16), injector (11), rotor shaft (8), vortex measurement of power
Machine (18), flow field survey equipment (19) carry out signal connection.
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| CN112945306A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Test platform for simultaneously measuring thrust and flow of double-duct spray pipe |
| CN113340604A (en) * | 2021-08-04 | 2021-09-03 | 中国飞机强度研究所 | High bypass ratio turbofan engine exhaust emission system |
| WO2021249186A1 (en) * | 2020-06-08 | 2021-12-16 | 清华大学 | High-efficiency, three-duct power propeller with high thrust-weight ratio |
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| CN113340604A (en) * | 2021-08-04 | 2021-09-03 | 中国飞机强度研究所 | High bypass ratio turbofan engine exhaust emission system |
| CN113959726A (en) * | 2021-09-21 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Power system of jet engine ground test platform |
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| CN114279714A (en) * | 2021-12-27 | 2022-04-05 | 北京航空航天大学 | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application |
| CN114279714B (en) * | 2021-12-27 | 2022-10-25 | 北京航空航天大学 | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application |
| CN114776871A (en) * | 2022-04-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Air entraining flow adjusting device of process spray pipe |
| CN115614177A (en) * | 2022-08-29 | 2023-01-17 | 中国航发四川燃气涡轮研究院 | Full-shielding mixing integrated casing |
| CN115614177B (en) * | 2022-08-29 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Full shielding blending integrated casing |
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| CN116380472A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Air inlet device in large bypass ratio engine core engine test |
| CN116380472B (en) * | 2023-06-05 | 2023-09-19 | 中国航发四川燃气涡轮研究院 | Air inlet device in large bypass ratio engine core engine test |
| CN117848729B (en) * | 2024-03-08 | 2024-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | Double culvert air suction type negative pressure test device |
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