CN103630363B - Test method and test device for simulating high altitude ignition ability of turbine engine - Google Patents
Test method and test device for simulating high altitude ignition ability of turbine engine Download PDFInfo
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- CN103630363B CN103630363B CN201310683784.8A CN201310683784A CN103630363B CN 103630363 B CN103630363 B CN 103630363B CN 201310683784 A CN201310683784 A CN 201310683784A CN 103630363 B CN103630363 B CN 103630363B
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Abstract
The invention discloses a simulation test method for high altitude ignition ability of a turbine engine. The method comprises high altitude performance test, high altitude distortion test, high altitude low-temperature test and highland starting test. A high altitude zero mach number test device of the turbine engine used by the method comprises a high altitude chamber, a calming pipe, a process air inlet channel, a turbine engine, a tail chamber, an air inlet pipe, and an air exhaust pipe, wherein the process air inlet channel is provided with a first air inlet and a first air outlet, the first air inlet and the outlet of the calming pipe are opposite and are separated, and the turbine engine is arranged in the high altitude chamber and is at the downstream side of the process air inlet channel. A distortion test device comprises a distortion simulator for the method, wherein the distortion simulator comprises a distortion simulation board and a turbine engine; the turbine engine is connected with the distortion simulator. The simulation test method for high altitude ignition ability of the turbine engine disclosed by the embodiment of the invention has the advantages of short cycle, low cost, and good practicability.
Description
Technical field
The present invention relates to engine art, more particularly, to a kind of simulation experiment method of turbogenerator high-altitude ignition ability
And assay device.
Background technology
Impact highly to turbogenerator service behaviour is essentially from two aspects: increases with height, atmospheric pressure drops
Low, Reynolds number raises, and exceedes critical Reynolds number rear engine component efficiencies and declines, leads to turbogenerator penalty or surge
Nargin reduces；On the other hand, due to reduced pressure, it is unfavorable for combustor tissue burning, turbogenerator may be led to stop working.Whirlpool
The aloft work performance of turbine itself is verified by the altitude test of altitude simulation unit and examines, but works as propeller for turboprop
After installing Submerged Inlet before machine, because Submerged Inlet has that total pressure recovery coefficient is low, total pressure distortion big, inlet air flow
Measure little feature, in starting process, air supply is undesirable, aircraft repeatedly occurs in big Mach number, Low Angle Of Attack condition in development
Lower turbogenerator fuel gas return-flow when starting, lead to the phenomenon of starting failure.
Study the turbogenerator high-altitude ignition ability with Submerged Inlet in correlation technique, typically pass through propulsion wind tunnel
Or empty station band fly test mode, but this mode cycle length, ensure complicated, costly.
Content of the invention
It is contemplated that at least solving one of above-mentioned technical problem.For this reason, it is an object of the present invention to proposing a kind of
The simulation experiment method of the turbogenerator high-altitude ignition ability of Submerged Inlet, the method cycle is short, low cost.
The simulation experiment method of the turbogenerator high-altitude ignition ability of the Submerged Inlet according to the present invention, including with
Lower step: according to the test of air intake duct blowing test according to number, the turbogenerator obtaining described Submerged Inlet is in different Mach
Number ma, angle of attack, yaw angle, discharge coefficientUnder inlet total pres sure recovery factor sigma and total pressure distortion degree w；According to described embedment
Turbogenerator working depth h of formula air intake duct and inlet air flow Mach number q (λ), obtain described Submerged Inlet and described
The operation interval of the turbogenerator associated working of Submerged Inlet；Described embedded type air inlet is obtained according to described operation interval
, in the range of operating envelope, under each state, the turbogenerator import of described Submerged Inlet is total for the turbogenerator in road
Pressure pt0 and total pressure distortion degree w, nozzle backpressure pc；Turbogenerator inlet distortion degree according to described Submerged Inlet
W, generates distortion simulation plate, and calculates degree of distortion wm that described distortion simulation plate produces and the stagnation pressure of described distortion simulation plate is extensive
Complex coefficient；Degree of distortion wm being produced according to described distortion simulation plate and the total pressure recovery coefficient regulation of described distortion simulation plate are abnormal
The air velocity becoming simulation plate exit is to determine between distortion simulation plate exit total pressure distortion degree ws and analog board blocked area
Functional relationship；According to ambient temperature ts, determine the working condition of the turbogenerator of Submerged Inlet described in aberration test
nh；The whirlpool of described Submerged Inlet under working condition nh of the turbogenerator according to described Submerged Inlet and this state
The inlet distortion degree w of turbine, determines the blocked area a of described distortion simulation plate, and according to described distortion simulation plate
Blocked area a adjust described distortion simulation plate；And after the regulation of described distortion simulation plate completes, carry out altitude respectively
Energy test, high-altitude aberration test, altitude low temperature test and plateau starting test.
The simulation experiment method cycle is short of the turbogenerator high-altitude ignition ability of the Submerged Inlet according to the present invention,
Low cost.
Distortion simulation plate produce degree of distortion wm meet following functional relationship: ws=f (q (λ), a).
The total pressure recovery coefficient of analog board meets following functional relationship: and σ m=g (q (λ), a)；Being demarcated by flow field can be true
Fixed: ws=f (q (λ), a), σ m=g (q (λ), a).
Functional relationship: a=f (q is met between distortion simulation plate exit total pressure distortion degree ws and analog board blocked area a
(λ), ws).
For completing the test of the simulation experiment method of the turbogenerator high-altitude ignition ability of described Submerged Inlet
Device, described assay device includes: stratochamber, and stratochamber includes nacelle and hatch door, and hatch door is pivotally arranged in nacelle to beat
Open or close and close nacelle, nacelle is formed with nacelle import and nacelle outlet；Stable pipe, stablizes pipe and is located in nacelle and is located at nacelle
Air inlet pipe installing port end, stablize first pipe and the second pipe that pipe includes being connected with each other, the sectional area of the cross section of first pipe is pressed
It is gradually increased according to the direction exporting towards nacelle from nacelle import, second pipe is the constant cylindrical tube of sectional area；Technique air inlet
Road, technique air intake duct is located in stratochamber and is located at the downstream stablizing pipe, and technique air intake duct has the first air inlet and first
Air vent, the first air inlet is relative with the outlet stablizing pipe and is spaced apart from each other, the central axis of technique air intake duct and stable pipe
Central axes；Turbogenerator, turbogenerator is located in stratochamber and is located at the downstream of technique air intake duct, starts
Machine has the second air inlet and second exhaust port, and the second air inlet is connected with first row QI KOU；Tail room, tail room is located in stratochamber
And the downstream positioned at electromotor, tail room has the 3rd air inlet and the 3rd air vent, the 3rd air inlet and second exhaust port pair
Should and be spaced apart from each other, tail room has the cooling section for cooling air；Air inlet pipe, one end of air inlet pipe is stretched into from nacelle import
It is connected in nacelle and with first pipe；Exhaustor, one end of exhaustor from nacelle outlet extend in nacelle and with the 3rd aerofluxuss
Mouth is connected.
Assay device also includes: air ejector, and air ejector is located at high-altitude and is connected out of my cabin and with exhaustor.
Assay device also includes: first support, stablizes pipe and is located in first support.
Assay device also includes: second support, and electromotor and technique air intake duct set on the secondary support bracket；3rd support, tail
Room is located on the 3rd support.
Assay device also includes: regulating valve, and regulating valve is located in air inlet pipe and is located at high-altitude out of my cabin；Stop valve, stop valve
It is located in air inlet pipe and be located at the upstream side of regulating valve；High altitude zero Mach number assay device for turbogenerator also includes:
For measuring the flow transducer from the flow stablizing the air that pipe flow goes out, the neighbouring technique that flow transducer is located at stable pipe is entered
On the side of air flue.
Assay device also includes aberration test device, and aberration test device includes: distortion simulator, distortion simulator
Including distortion simulation plate；Turbogenerator, turbogenerator is connected with distortion simulator.
Brief description
The above-mentioned and/or additional aspect of the present invention and advantage will become from the following description of the accompanying drawings of embodiments
Substantially and easy to understand, wherein,
Fig. 1 is the signal of the zero Mach number assay device for turbogenerator according to an embodiment of the invention
Figure；
Fig. 2 is the signal of the zero Mach number assay device for turbogenerator according to an embodiment of the invention
Figure；
Fig. 3 is that the zero Mach number assay device for turbogenerator according to an embodiment of the invention completes to test
Parameters variation diagram afterwards；
Fig. 4 is the mould of the turbogenerator high-altitude ignition ability of Submerged Inlet according to an embodiment of the invention
Intend the schematic flow sheet of test method；
Fig. 5 is the mould of the turbogenerator high-altitude ignition ability of Submerged Inlet according to an embodiment of the invention
Intend the principle schematic of test method；
Fig. 6 is the schematic diagram of aberration test device according to an embodiment of the invention.
Reference list:
High altitude zero Mach number assay device 100 for turbogenerator；Stratochamber 1；Nacelle 11；Nacelle import 111；Cabin
Body outlet 112；Hatch door 12；Second support 14；3rd bracket stable pipe 2；First pipe 21；Second pipe 22；Technique air intake duct 3；The
One air inlet 31；Turbogenerator 4；Second exhaust port 41；Tail room 5；3rd air inlet 51；Cooling section 53；Air inlet pipe 6；Aerofluxuss
Pipe 7；Regulating valve 8；Stop valve 9；Air ejector 10；Stagnation temperature measuring section 201；Total pressure measurement section 202；Deng straight section 203；Abnormal
Become analog 204；Linkage section 205；Tail rake 207.
Specific embodiment
Embodiments of the invention are described below in detail, the example of described embodiment is shown in the drawings, wherein from start to finish
The element that same or similar label represents same or similar element or has same or like function.Below with reference to attached
The embodiment of figure description is exemplary, is only used for explaining the present invention, and is not considered as limiting the invention.
In describing the invention it is to be understood that term " " center ", " longitudinal ", " horizontal ", " on ", D score,
The orientation of instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " or position relationship are
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description, rather than instruction or dark
Show the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that right
The restriction of the present invention.Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint are relative
Importance or the implicit quantity indicating indicated technical characteristic.Thus, define " first ", the feature of " second " can be bright
Show or implicitly include one or more this feature.In describing the invention, unless otherwise stated, the containing of " multiple "
Justice is two or more.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or is integrally connected；Can
To be to be mechanically connected or electrical connection；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
Describe the high null point of turbogenerator according to the Submerged Inlet of the present invention below with reference to Figure of description in detail
The simulation experiment method of fiery ability.
The simulation experiment method of the turbogenerator high-altitude ignition ability of the Submerged Inlet according to the present invention, with reference to figure
1 and Fig. 5, comprise the following steps:
S1: according to the test of air intake duct blowing test according to number, the turbogenerator obtaining Submerged Inlet is in different Mach
Number ma, angle of attack, yaw angle, discharge coefficientUnder inlet total pres sure recovery factor sigma and total pressure distortion degree w.
S2: turbogenerator working depth h according to Submerged Inlet and inlet air flow Mach number q (λ), obtain embedment
The operation interval of the turbogenerator associated working of formula air intake duct and Submerged Inlet.
S3: the turbogenerator of Submerged Inlet is obtained in the range of operating envelope according to operation interval, each state
The stagnation pressure pt0 of the turbogenerator import of lower Submerged Inlet and total pressure distortion degree w, nozzle backpressure pc.
S4: according to the turbogenerator inlet distortion degree w of Submerged Inlet, generate distortion simulation plate, and calculate
Degree of distortion wm and the total pressure recovery coefficient σ m of distortion simulation plate that distortion simulation plate produces.
S5: degree of distortion wm being produced according to distortion simulation plate and the total pressure recovery coefficient σ m of distortion simulation plate adjust distortion
The air velocity of simulation plate exit is to determine the letter between distortion simulation plate exit total pressure distortion degree ws and analog board blocked area
Number relation.
S6: according to ambient temperature ts, determine working condition nh of the turbogenerator of Submerged Inlet in aberration test.
The whirlpool of Submerged Inlet under s7: working condition nh of the turbogenerator according to Submerged Inlet and this state
The inlet distortion degree w of turbine, determines the blocked area a of distortion simulation plate, and the blocking face according to distortion simulation plate
Long-pending a adjusts distortion simulation plate.
S8: after distortion simulation plate adjusts and completes, carry out upper air performance, high-altitude aberration test, high-altitude respectively low
Temperature test and plateau starting test.
It should be noted that above-mentioned steps s1-s8 illustrate order be not step s1-s8 must strictly in accordance with enforcement
Sequentially, step s1-s8 can not be carried out according to above-mentioned shown order.
Wherein, in step s4, degree of distortion wm that distortion simulation plate produces meets following functional relationship:
Wm=f (q (λ), a) --- --- --- --- --- --- -- (1)
Wherein, wm is the degree of distortion that distortion simulation plate produces；
Q (λ) is the inlet air flow Mach number of the turbogenerator of Submerged Inlet；
A is the blocked area a of distortion simulation plate.
In step s5, distortion simulation plate also can produce certain pressure loss, total pressure recovery coefficient σ of distortion simulation plate
M meets following functional relationship:
σ m=g (q (λ), a) --- --- --- --- --- --- ----(2)
Wherein, σ m is the total pressure recovery coefficient of distortion simulation plate；
Q (λ) is the inlet air flow Mach number of the turbogenerator of Submerged Inlet；
A is the blocked area a of distortion simulation plate；
Above-mentioned functional relationship (1) (2) can be demarcated by flow field and be obtained.That is, distortion simulation plate mark can be passed through
Fixed number is according to determining functional relationship (1) (2).
In step s7, meet function between distortion simulation plate exit total pressure distortion degree ws and analog board blocked area a and close
System:
A=f (q (λ), ws) --- --- --- --- --- --- --- --- -- (3)
Wherein, q (λ) is the inlet air flow Mach number of the turbogenerator of Submerged Inlet；
A is the blocked area a of distortion simulation plate；
Ws is distortion simulation plate exit total pressure distortion degree.
Study the ability to work in electromotor high-altitude by upper air performance, this test can complete in altitude simulation unit；Root
According to the operating envelope of aircraft, simulate working depth envelope curve and the flight Mach number envelope curve of turbogenerator in test, that is,
The engine intake stagnation pressure pt0 determining and nozzle backpressure pc.
High-altitude inlet engine compatibility after installing Submerged Inlet before turbogenerator is studied by the anti-aberration test in high-altitude
Energy.According to flying height h, Mach number ma, ambient temperature ts in test, determine working condition nh of aberration test electromotor；Root
According to electromotor inlet distortion degree w under engine behavior and this state, determine the blocked area a of distortion simulation plate；Root
According to total pressure recovery coefficient and flying height h, the Mach number ma of analog board, determine the air-flow stagnation pressure pt0/ σ before analog board.
By altitude low temperature starting test, study starting capability under the conditions of altitude low temperature for the electromotor.Start in test
Machine is placed in cryostat, and after engine turbine, temperature reaches insulation 2h after minimum temperature requirement until hygral equilibrium, then
Simulated altitude pc, incoming-flow pressure pt0, carry out test flowing low temperature ts, test camber, temperature, Mach number should be chosen the harshest
Envelope curve.
Plateau starting test is the starting checking under the conditions of engine intake no speed punching press, can be studied by this test
The reasonability of electromotor startup control law under the conditions of the low total pressure recovery coefficient of Submerged Inlet.Test height should be and starts
The height envelope curve the harshest of machine work, free stream Mach number should ensure that no more than 0.1；In test electromotor should occur without suspension,
The phenomenons such as delay.
In a specific embodiment of invention, determined according to air intake duct blowing data and fly in electromotor operating envelope
Line height h is 6km and flight Mach number ma is that air intake port total pressure distortion degree w when 0.7 is 8.5% and inlet total pressure is extensive
Complex coefficient σ is 0.93.Submerged Inlet and Engine Matching work calculating obtain engine intake air-flow stagnation pressure pt0 and are
61.4kpa and total pressure distortion degree w is 8.5%, nozzle backpressure is 47.2kpa.
Total pressure distortion degree w according to engine intake is 8.5%, have developed the pressure distortion simulation of certain blocked area
Plate.By demarcating the functional relationship obtaining between the blocked area a of analog board and total pressure distortion w and total pressure recovery coefficient σ.
It is -23.9 DEG C according to ambient temperature, determine engine behavior rotating speed nh=nh* × sqrt (249.2/
288.15) the total pressure distortion degree that, generation is worth for 8.5% under this working condition needs the blocked area a of analog board.
Then electromotor can be carried out in flying height h is the high-level performance examination that 6km, flight Mach number ma are 0.5～0.8
Test, in test, nozzle backpressure is modeled as engine intake stagnation pressure when 47.2kpa, Mach 2 ship 0.7 is 61.4kpa.
Carry out the anti-aberration test in high-altitude that flying height h is that 6km, flight Mach number ma are 0.5, pacify before electromotor in test
Dress distortion simulation plate, the area that gets lodged in of analog board is a, and nozzle backpressure is 47.2kpa, and before analog board, pressure is (56.4/0.899)
kpa.
Carry out flying height h be 6km, flight Mach number ma be 0.5, the temperature of turbogenerator body be -45 DEG C, air inlet
The altitude low temperature test of -50 DEG C of temperature.After temperature reaches -45 DEG C after the turbine of turbogenerator, it is incubated 2h up to hygral equilibrium,
Then simulate nozzle backpressure pc be 47.2kpa, incoming-flow pressure be 56.4kpa, come to flow low temperature be -50 DEG C when tested.
Carry out flying height h to test for 6km plateau starting.This experiment can be in the zero Mach number test for turbogenerator
Carry out in device.
The turbogenerator of Submerged Inlet, after above-mentioned development test step, shows this etc. through flight test examination
Effect test is true, effectively.
The zero Mach number assay device for turbogenerator can be used for completing the turbogenerator height of Submerged Inlet
The simulation experiment method of empty ignition ability, is especially useful in plateau starting test.
Below with reference to Figure of description, the high altitude zero Mach number for turbogenerator according to embodiments of the present invention is described
Assay device 100.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention, including stratochamber
1st, pipe 2, technique air intake duct 3, turbogenerator 4, tail room 5, air inlet pipe 6 and exhaustor 7 are stablized.
Wherein, stratochamber 1 includes nacelle 11 and hatch door 12, and hatch door 12 is pivotally arranged in nacelle 11 to open or close
Nacelle 11, nacelle 11 is formed with nacelle import 111 and nacelle outlet 112.One end of air inlet pipe 6 is stretched into from nacelle import 111
To in nacelle 11.
Stablize pipe 2 to be located in nacelle 11 and be located at nacelle import 111 end of nacelle 11.Stablize what pipe 2 included being connected with each other
First pipe 21 and second pipe 22, the sectional area of the cross section of first pipe 21 exports 112 according to from nacelle import 111 towards nacelle
Direction is gradually increased, and for example in the example of fig. 1, the sectional area of the cross section of first pipe 21 is gradually increased from left to right, and that is,
One pipe 21 is formed as substantially infundibulate, and second pipe 22 is the constant cylindrical tube of sectional area that is to say, that the horizontal stroke of second pipe 22
The sectional area in section is constant.
One end of air inlet pipe 6 is extend in nacelle 11 from nacelle import 111 and is connected with first pipe 21.Enter from air inlet pipe 6
Enter the air in nacelle 11 and initially enter stable pipe 2.It is understood that when test, air can be from stablizing pipe 2 with relatively
Low speed projects, and the Mach number of such as air inlet is not more than 0.05, i.e. ma ≮ 0.05, wherein symbol " ≮ " implication be
" no more than ".
Stablize pipe 2 for steady air flow that is to say, that test when, from stablize pipe 2 discharge stream pressure and stream
Speed is substantially constant constant, and such turbogenerator 4 ensure that stablizing of inlet air conditions in starting process, realizes Mach
Number is substantially constant.
Technique air intake duct 3 is located in stratochamber 1 and is located at the downstream stablizing pipe 2.Downstream refers to empty in nacelle 11
Right side in the downstream in flow of air direction, such as Fig. 1 and Fig. 2 is downstream that is to say, that technique is entered in fig. 1 and 2
Air flue 3 is located at the right side of stable pipe 2." downstream " hereinafter occurring again, if not making specified otherwise, all pressing this and understanding.
Technique air intake duct 3 has the first air inlet 31 and first row QI KOU, the first air inlet 31 and the outlet phase stablizing pipe 2
To and be spaced apart from each other.The part stablizing the air of the stable output of pipe 2 enters technique air intake duct 3 simultaneously by the first air inlet 31
Enter turbogenerator 4, remaining most of air-flow flows through outside technique air intake duct 3, and is gone out stratochamber 1 by tail room 5 suction.The
One air vent is connected with turbogenerator 4, and the air in technique air intake duct 3 flows in turbogenerator 4 through first row QI KOU.
So allow turbogenerator 4 natural aspiration in starting process, and stablize the stream pressure of pipe 2 discharge and flow velocity be stablize constant
, thus can realize the steady of intake simulation Mach number.
The central axis of technique air intake duct 3 and the central axes stablizing pipe 2.So can better ensure that pressure and
The air of flow speed stability flows into technique air intake duct 3 hence into turbogenerator 4.
Turbogenerator 4 is located in stratochamber 1 and is located at the downstream of technique air intake duct 3, that is, the right side in Fig. 1.
Turbogenerator 4 has the second air inlet and second exhaust port 41, and the second air inlet is connected with first row QI KOU.?
That is, the air in technique air intake duct 3 flows in turbogenerator 4 through first row QI KOU and the second air inlet.Can manage
Solution, turbogenerator 4 has been prior art, and known to those of ordinary skill in the art, therefore here for turbine
The specific configuration of electromotor 4 and operation principle do not elaborate.
Tail room 5 is located in stratochamber 1 and is located at the downstream of turbogenerator 4, that is, the right side in Fig. 1.
Tail room 5 has the 3rd air inlet 51 and the 3rd air vent, the 3rd air inlet 51 corresponding with second exhaust port 41 and that
This is spaced apart.The air that turbogenerator 4 is discharged enters tail room 5 by the 3rd air inlet 51.
Tail room 5 has the cooling section 53 for cooling air, and the 3rd air vent is located at the afterbody of cooling section 53.Propeller for turboprop
The high-temperature gas that machine 4 is discharged is cooled and from the 3rd air vent discharge in cooling section 53.
One end of air inlet pipe 6 is extend in nacelle 11 from nacelle import 111 and is connected with first pipe 21, air inlet pipe 6 another
One end is connected with source of the gas, and air inlet pipe 6 imports to the air in source of the gas in nacelle 11.
One end of exhaustor 7 is extend in nacelle 11 and is connected with the 3rd air vent from nacelle outlet 112.That is,
Exhaustor 7 is connected with cooling section 53, and the air after cooling section 53 cooling is discharged outside nacelle 11 by exhaustor 7.
At the trial, to certain numerical value, such as the pressure in stratochamber 1 is the pressure first in adjustment stratochamber 1
60.2kpa, simultaneously air inlet pipe 6 input the air with certain pressure into stratochamber 1, air becomes flat by stablizing after pipe 2
Surely, adjust air mass flow, for example, air mass flow can be 4kg/s.After stratochamber 1 intake and exhaust balance, formed in stratochamber 1
It is stable that from stablizing the gas channel to tail room 5 for the pipe 2, fraction flows into turbogenerator 4 by technique air intake duct 3, remaining
Most of air-flow flows through outside turbogenerator 4.At this moment the windmill rotating speed of turbogenerator 4 is zero, and air inlet Mach number is about
0.03, equivalent wind speed is about 36km/h., for turbogenerator 4, air-flow punching press effect does not almost have, and is equivalent to no wind speed for this
Under the conditions of starting, that is, be equivalent to zero Mach number start.So turbogenerator 4 just can complete heat run according to existing procedure
Content of the test.After turbogenerator 4 stops, continue supply after turbogenerator 4 temperature reduces, stop supply, test knot
Bundle.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention is by entering technique
Air flue 3 and stablize pipe 2 and be spaced apart, allows turbogenerator 4 natural aspiration in starting process, thus realizing intake simulation Mach number
Steady, may then pass through adjust stratochamber 1 in pressure and air mass flow, it is possible to achieve for turbogenerator 4 zero horse
The experiment condition of conspicuous number, quickly realizes turbogenerator 4 such that it is able to low cost and starts examination in the state of ground zero Mach number
Test, practicality is good.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention also includes air and draws
Emitter 10.Air ejector 10 is located at outside stratochamber 1 and is connected with exhaustor 7 to aspirate the air in nacelle 11, adjusts nacelle
Pressure in 11, makes the pressure in stratochamber 1 reach the pressure of needs.
Additionally, turbogenerator 4 ignition start arrives in the state of the pressure in stratochamber 1 and air mass flow all regulate
Slow train operating mode, in turbogenerator 4 starting process, because turbogenerator 4 aerofluxuss are from ejector action, can reduce stratochamber
1 pressure, makes the pressure in stratochamber 1 produce fluctuation, adjusts the pressure that air ejector 10 can stablize stratochamber 1.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention also includes first
Frame.Stablize pipe 2 to be located in first support.So can ensure that the stability of stable pipe 2, improve stability and the reliability of experiment
Property.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention also includes second
Frame 14 and the 3rd support.
Wherein, turbogenerator 4 and technique air intake duct 3 are located in second support 14.Tail room 5 is located on the 3rd support.
Second support 14 is provided with hanger bracket, and turbogenerator 4 can be suspended on hanger bracket.
Pressure transducer can be provided with second support 14, this pressure transducer is used for measuring the pressure in stratochamber 1, with
Just adjust the pressure in stratochamber 1 as needed, reach the requirement of experiment condition.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention also includes regulating valve
8 and stop valve 9.
Wherein regulating valve 8 is located in air inlet pipe 6 and is located at outside stratochamber 1.Regulating valve 8 can adjust the air coming from source of the gas
Flow make the air mass flow in stratochamber 1 reach the required air stream under zero Mach number experiment condition of turbogenerator 4
Amount.
Stop valve 9 is located in air inlet pipe 6 and is located at the upstream side of regulating valve 8.That is, stop valve 9 is calmed the anger in being located at
Between source and regulating valve 8, air inlet pipe 6 can be closed and open air inlet pipe 6, so can preferably adjust charge flow rate, it is to avoid
The frequent opening and closing of regulating valve 8, extends the service life of regulating valve 8.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention is also included for surveying
The flow transducer of the flow from the air stablizing pipe 2 outflow for the amount, flow transducer is located at the neighbouring technique air intake duct of stable pipe 2
To measure air mass flow on 3 side.
In one embodiment of the invention, the high altitude zero Mach number for turbogenerator according to embodiments of the present invention
Assay device 100 also includes controller, and controller can be connected with flow transducer and regulating valve 8, and flow transducer transmits flow
To controller, controller can control to adjust valve 8 to signal, and the flow adjusting the therefrom air that pressurized air source comes makes air mass flow reach
Flow required by turbogenerator 4 air inlet.
High altitude zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention also includes air intake duct
Pressure transducer.Inlet pressure sensor can be multiple, and one of inlet pressure sensor may be provided in technique air intake duct 3
The first air inlet 31 near, for measuring turbogenerator 4 air intake duct wall static pressure.At least three inlet pressures are also had to pass
Sensor is uniformly distributed along air inlet cross-section radial, for measuring turbogenerator 4 inlet total pressure.
The zero Mach number assay device 100 for turbogenerator according to embodiments of the present invention is also included for measuring whirlpool
The speed probe of turbine 4 rotating speed.
The process of the test of zero Mach number assay device 100 in accordance with a preferred embodiment of the present invention is briefly described below.
First, open air ejector 10, the pressure in adjustment stratochamber 1, to 60.2kpa, opens stop valve 9 simultaneously, control
Regulating valve 8 processed, makes air inlet pipe 6 be blown into, by stablizing pipe 2, the air that air mass flow is 4kg/s into stratochamber 1.When stratochamber 1
After intake and exhaust balance, formed in stratochamber 1 stable from stablizing the gas channel to tail room 5 for the pipe 2, fraction is entered by technique
Air flue 3 flows into turbogenerator 4, and remaining most of air-flow flows through outside turbogenerator 4.At this moment the wind of turbogenerator 4
Car rotating speed is zero, and air inlet Mach number is about 0.03, and equivalent wind speed is about 36km/h.This air-flow punching press for turbogenerator 4
Effect does not almost have, and therefore for turbogenerator 4, is equivalent to the starting under the conditions of no wind speed.State in zero Mach number
After simulation is good, to slow train operating mode, turbogenerator 4 starting process is because aerofluxuss are from injection work for turbogenerator 4 ignition start
With the pressure in stratochamber 1 can be reduced, and needs to stablize the pressure oscillation of stratochamber 1 by adjusting air ejector 10.High-altitude
After the pressure stability in cabin 1, turbogenerator 4 continues to complete other heat run contents of the test according to intended flow.Turbogenerator 4
After parking, continue supply after the reduction of turbogenerator 4 temperature, stop supply off-test.
By above-mentioned experiment, following result of the test can be drawn, its curve chart is as shown in Figure 3:
Wherein, pm1 is engine inlets wall static pressure；Pc1 is stratochamber 1 ambient pressure；N is engine speed；
Ptm1, ptm2, ptm3 are the engine charge stagnation pressure along equally distributed three points of air inlet cross-section radial；T0 is turbogenerator
In 4 starting moment, t1 is a certain moment after turbogenerator 4 starting.
Inlet pressure sensor can measure and draw pm1 value, that is, engine inlets wall static pressure；In second support
Pressure transducer on 14 can measure and draw pc1 value, that is, stratochamber 1 ambient pressure；Speed probe can measure and draw n
Value, that is, engine speed；At least three can survey respectively along air inlet cross-section radial equally distributed inlet pressure sensor
Measure out ptm1, ptm2, ptm3, that is, the engine charge stagnation pressure along equally distributed three points of air inlet cross-section radial.
With reference to Fig. 3, turbogenerator 4 prestart, in turbogenerator 4 inlet total pressure and stratochamber 1, pressure is more steady,
And pressure value is essentially identical, illustrate that turbogenerator 4 is relatively low come flow velocity, the no obvious punching press effect of air-flow.Turbogenerator 4
In the dynamic moment, air inlet is come with stream certain interference, but absolute figure very little, the parameters satisfaction examination of simulation from result of the test
Test simulation to require.
Thus, propeller for turboprop can be simulated by zero Mach number assay device 100 according to an embodiment of the invention
Intake and exhaust condition under high altitude zero Mach number for the machine 4, such that it is able to simulate for aircraft turbogenerator 4 under this condition
Starting performance, the startup control law under the conditions of turbogenerator 4 is directed to this is optimized, it is possible to achieve expected test mesh
's.Meanwhile, using zero Mach number assay device 100 simulation test low cost according to an embodiment of the invention, practicality is good.
Describe the turbogenerator high-altitude ignition energy for Submerged Inlet according to the present invention below with reference to Fig. 6 in detail
The aberration test device of the simulation experiment method of power, the anti-aberration test in high-altitude can complete in this aberration test device.
This aberration test device includes: distortion simulator 204 and turbogenerator 4.
Wherein, distortion simulator 204 includes distortion simulation plate, and distortion simulation plate can need to adjust blocking face according to experiment
Long-pending a.
Turbogenerator 4 is connected with distortion simulator 204.
This aberration test device may also include stagnation temperature measuring section 201, total pressure measurement section 202, etc. straight section 203, connect
Section 205 and tail rake 207.Wherein, ambient temperature can be measured in stagnation temperature measuring section 201, and total static pressure can be in total pressure measurement
Section 202 is measured.Turbogenerator 4 is located between linkage section 205 and tail rake 207, and distortion simulator 204 is located at linkage section
205 and wait between straight section 203.
In the description of this specification, reference term " embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means specific features, the knot describing with reference to this embodiment or example
Structure, material or feature are contained at least one embodiment or the example of the present invention.In this manual, to above-mentioned term
Schematic representation is not necessarily referring to identical embodiment or example.And, the specific features of description, structure, material or spy
Point can combine in any one or more embodiments or example in an appropriate manner.
Although an embodiment of the present invention has been shown and described, it will be understood by those skilled in the art that: not
Multiple changes, modification, replacement and modification can be carried out to these embodiments in the case of the principle of the disengaging present invention and objective, this
The scope of invention is limited by claim and its equivalent.
Claims (10)
1. a kind of simulation experiment method of the turbogenerator high-altitude ignition ability of Submerged Inlet is it is characterised in that include
Following steps:
According to air intake duct blowing test according to number, obtain the turbogenerator of described Submerged Inlet in different Mach number ma, attack
Angle α, yaw angle, discharge coefficientUnder inlet total pres sure recovery factor sigma and total pressure distortion degree w；
Turbogenerator working depth h according to described Submerged Inlet and inlet air flow Mach number q (λ), bury described in acquisition
Enter the operation interval of the turbogenerator associated working of formula air intake duct and described Submerged Inlet；
The turbogenerator of described Submerged Inlet is obtained in the range of operating envelope according to described operation interval, each state
Under the stagnation pressure pt0 of turbogenerator import of described Submerged Inlet and total pressure distortion degree w, nozzle backpressure pc；
According to the turbogenerator inlet distortion degree w of described Submerged Inlet, generate distortion simulation plate, and calculate described
Degree of distortion wm and the total pressure recovery coefficient σ m of described distortion simulation plate that distortion simulation plate produces；
Degree of distortion wm being produced according to described distortion simulation plate and the total pressure recovery coefficient σ m regulation of described distortion simulation plate are abnormal
The air velocity becoming simulation plate exit is to determine between distortion simulation plate exit total pressure distortion degree ws and analog board blocked area
Functional relationship；
According to ambient temperature ts, determine working condition nh of the turbogenerator of Submerged Inlet described in aberration test；
Described Submerged Inlet under working condition nh of the turbogenerator according to described Submerged Inlet and this state
The inlet distortion degree w of turbogenerator, determines the blocked area a of described distortion simulation plate, and according to described distortion simulation
The blocked area a of plate adjusts described distortion simulation plate；
After the regulation of described distortion simulation plate completes, carry out upper air performance, high-altitude aberration test, altitude low temperature examination respectively
Test and plateau starting test.
2. the simulation experiment method of the turbogenerator high-altitude ignition ability of Submerged Inlet according to claim 1,
It is characterized in that, degree of distortion wm that distortion simulation plate produces meets following functional relationship:
Wm=f (q (λ), a).
3. the simulation experiment method of the turbogenerator high-altitude ignition ability of Submerged Inlet according to claim 1,
It is characterized in that, the total pressure recovery coefficient σ m of analog board meets following functional relationship:
σ m=g (q (λ), a)；
By flow field demarcate determine wm=f (q (λ), a), σ m=g (q (λ), a).
4. the simulation experiment method of the turbogenerator high-altitude ignition ability of Submerged Inlet according to claim 1,
It is characterized in that, meet functional relationship between distortion simulation plate exit total pressure distortion degree ws and analog board blocked area a:
A=f (q (λ), ws).
5. a kind of assay device is it is characterised in that described assay device is used for completing the embedment described in any one of claim 1-4
The simulation experiment method of the turbogenerator high-altitude ignition ability of formula air intake duct, described assay device includes:
Stratochamber, described stratochamber includes nacelle and hatch door, and described hatch door is pivotally arranged in and is opened or closed with beating in described nacelle
Close described nacelle, described nacelle is formed with nacelle import and nacelle outlet；
Stable pipe, described pipe of stablizing is located in described nacelle and is located at the nacelle entrance point of described nacelle, and described pipe of stablizing includes
The first pipe being connected with each other and second pipe, the sectional area of the cross section of described first pipe according to from described nacelle import towards described
The direction of nacelle outlet is gradually increased, and described second pipe is the constant cylindrical tube of sectional area；
Technique air intake duct, described technique air intake duct is located in described stratochamber and is located at the described downstream stablizing pipe, described work
Skill air intake duct has the first air inlet and a first row QI KOU, and described first air inlet is relative with the described outlet stablizing pipe and each other
It is spaced apart, the central axis of described technique air intake duct and the described central axes stablizing pipe；
Turbogenerator, described turbogenerator is located in described stratochamber and is located at the downstream of described technique air intake duct, institute
State electromotor and there is the second air inlet and second exhaust port, described second air inlet is connected with described first row QI KOU；
Tail room, described tail room is located in described stratochamber and is located at the downstream of described electromotor, and described tail room has the 3rd and enters
QI KOU and the 3rd air vent, described 3rd air inlet is corresponding with described second exhaust port and is spaced apart from each other, and described tail room has
Cooling section for cooling air；
Air inlet pipe, one end of described air inlet pipe is extend in described nacelle from described nacelle import and is connected with described first pipe；
Exhaustor, one end of described exhaustor from the outlet of described nacelle extend in described nacelle and with described 3rd air vent phase
Even.
6. assay device according to claim 5 is it is characterised in that also include: air ejector, described air ejector
It is located at described high-altitude to be connected out of my cabin and with described exhaustor.
7. assay device according to claim 5 is it is characterised in that also include: first support, and described pipe of stablizing is located at institute
State in first support.
8. assay device according to claim 5 is it is characterised in that also include:
Second support, described electromotor and described technique air intake duct are located in described second support；
3rd support, described tail room is located on described 3rd support.
9. assay device according to claim 5 is it is characterised in that also include:
Regulating valve, described regulating valve is located in described air inlet pipe and is located at described high-altitude out of my cabin；
Stop valve, described stop valve is located in described air inlet pipe and is located at the upstream side of described regulating valve；
For measuring the flow transducer from the described flow stablizing the air that pipe flow goes out, described flow transducer is located at described steady
On the side of neighbouring described technique air intake duct of fixed tube.
10. assay device according to claim 5 is it is characterised in that also include:
Distortion simulator, described distortion simulator includes distortion simulation plate；
Turbogenerator, described turbogenerator is connected with described distortion simulator.
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