CN106198030B - Tail room for engine testsand exhaust system - Google Patents
Tail room for engine testsand exhaust system Download PDFInfo
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- CN106198030B CN106198030B CN201610772826.9A CN201610772826A CN106198030B CN 106198030 B CN106198030 B CN 106198030B CN 201610772826 A CN201610772826 A CN 201610772826A CN 106198030 B CN106198030 B CN 106198030B
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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
- G01M15/02—Details or accessories of testing apparatus
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- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of tail rooms for engine testsand exhaust system, tail room includes big tail room and replaceable small tail room, and big tail room includes the tail room converging portion of connection, the straight sections such as tail room and tail room expansion segment, replaceable small tail room setting is connect in the converging portion of tail room, and with tail room converging portion；The straight sections such as tail room converging portion, tail room, tail room expansion segment and replaceable small tail room are hollow revolving body；Engine with nozzle and tail room converging portion are arranged in altitude simulation cabin, the setting of tail room expansion segment altitude simulation out of my cabin, engine is supersonic speed engine.The tail room of the present invention, improves follow-up air-extractor and passively flows into a mouthful static pressure, reduce follow-up air-extractor pressure ratio, and then reduce the injector series of follow-up air-extractor or the volume of vacuum tank, meanwhile being arranged and replacing small tail cell structure, meet the demand of sizes engine test.
Description
Technical field
The present invention relates to a kind of tail rooms for engine testsand exhaust system, especially a kind of to start for supersonic speed
The tail room of machine test bay exhaust system.
Background technology
In ground simulation supersonic speed engine high-altitude flight state, engine is first usually mounted on altitude simulation cabin
It is interior, use air-extractor to carry out residing height when pumping makes the pressure in altitude simulation cabin with engine high-altitude flight to stratochamber
The environmental pressure of degree is identical, then carries out engine ignition, carries out high-altitude flight simulation test, to remain during the test
The residing environmental pressure of height is identical when pressure in altitude simulation cabin is with engine high-altitude flight, this is just needed Supersonic immediately
The gas discharge altitude simulation cabin of fast engine discharge, in the prior art, generally use injector or vacuum tank are evacuated, and
The pressure of altitude simulation out of my cabin is usually 0.11MPa, and the environmental pressure of supersonic speed engine flight height is only then atmospheric pressure
0.1 times of power or even 0.01 times, the pressure ratio of exhaust system will reach 10 to 100, and the flow of corresponding exhaust system import is every
Second is then up to more than ten kilograms even up to a hundred kilograms, and pressure ratio big in this way and by draught jet capacity only leans on the supercharging of injector, it is necessary to
Three connect to level Four, if using vacuum tank, the volume of vacuum tank will be up to upper ten thousand stere, it can be seen that, no matter individually
Using injector or vacuum tank as air-extractor, it is required to huge structure, not only inefficiency, expense is also sufficiently expensive；
Secondly, engine testsand usually need to carry out high-altitude flight simulation, and different engines, the ruler of engine to various engines
Very little, nozzle size, engine export flow are different, using a set of air-extractor, cannot be satisfied various engines
Test requirements document.
Invention content
The purpose of the invention is to overcome the problems of the above-mentioned prior art and provide a kind of to spray engines tail
The kinetic energy of pipe effectively stagnation, improves follow-up air-extractor and passively flows into a mouthful static pressure, reduce the supercharging needed for follow-up air-extractor
Than, while the tail room of applicable sizes engine test.
The purpose of the present invention can be achieved through the following technical solutions：
A kind of tail room for engine testsand exhaust system, the tail room include fixed big tail room and replaceable small tail
Room, according to nozzle exiting exhaust gas flow direction, the big tail room of fixation includes the tail room being coaxially fixedly connected sequentially
Converging portion, the straight sections such as tail room and tail room expansion segment, the replaceable small tail room are arranged in the converging portion of the tail room, and with it is described
Tail room converging portion is fixedly and coaxially connected；The straight sections such as tail room converging portion, tail room, tail room expansion segment and replaceable small tail room are
Hollow revolving body；Engine and tail room converging portion with nozzle are arranged in altitude simulation cabin, the tail
The setting of room expansion segment altitude simulation out of my cabin, the engine is supersonic speed engine.
Further, the water-spraying control being provided on fixed big tail room for cooling down nozzle exiting exhaust gas fills
It sets.
Further, the replaceable small tail room includes the small tail room flange being fixedly and coaxially connected and small tail room cylinder, institute
It states small tail room cylinder to be arranged in the converging portion of the tail room, the small tail room flange and is fixed at tail room converging portion and enters
The big tail room flange of fixation of mouth is bolted to connection.
Further, a diameter of D of the tail room converging portion entrancew, convergency αwr；The diameter of the straight sections such as the tail room
Dwkp, length Lwkp；A diameter of D of tail room expansion segment outletwc, angle of flare αwc；The Dw, Dwkp, LwkpMeet following
Equation group：
Lwkp=4Dwkp(7)；
In above-mentioned equation group：Mw：Tail room converging portion entrance Mach number；k：Specific heat ratio；π(Mw)：Tail room converging portion entrance Mach
The corresponding static pressure of number and stagnation pressure ratio；Pw：The corresponding static pressure of tail room converging portion entrance Mach number, unit pa；Pt5：It restrains tail room
The corresponding stagnation pressure of section entrance Mach number, unit pa；Dw：The diameter of tail room converging portion entrance, unit mm；d4kp：Engine larynx
Road diameter, unit mm；After the corresponding normal shock wave of tail room converging portion entrance Mach number with the overall pressure tatio before normal shock wave；q
(Mw)：The corresponding velocity coeffficient of tail room converging portion entrance Mach number；Dwkp：The diameter of the straight sections such as tail room, unit mm；Lwkp：Tail
The length of the straight sections such as room, unit mm；
Wherein, true environment when the corresponding static pressure of tail room converging portion entrance Mach number is with supersonic speed engine high-altitude flight
Pressure is identical, the outlet Mach of the corresponding stagnation pressure of tail room converging portion entrance Mach number and the nozzle of supersonic speed engine
The corresponding stagnation pressure of number is identical, and the nozzle exit Mach number of supersonic speed engine is more than 1, and supersonic speed engine starts
Tail nozzle exit Mach number, the corresponding stagnation pressure of nozzle exit Mach number of supersonic speed engine, supersonic speed are started
True environmental pressure when machine high-altitude flight, specific heat ratio and supersonic speed engine throat diameter are that supersonic speed engine is intrinsic
Known parameters, the parameter in above-mentioned equation group：Mw, k, π (Mw), Pw, Pt5, Ww, d4kp,q(Mw), Dwkp, LwkpIt is Supersonic
In the supersonic speed engine of all experiments of fast nozzle exhaust simulation test, nozzle rate of discharge is maximum
The corresponding parameter of supersonic speed engine.
Further, the convergency meets：0 ＜ αwr≤12°；The angle of flare meets 0 ＜ αwc≤12°。
Further, a diameter of D of the replaceable small tail roomwx, the DwxMeet following equations group：
In above-mentioned equation group：Mwx：Replaceable small tail chamber inlet Mach number；π(Mwx)：Replaceable small tail chamber inlet Mach number
Corresponding static pressure and stagnation pressure ratio；Pwx：The corresponding static pressure of replaceable small tail chamber inlet Mach number, unit pa；Pt5x：It is replaceable
The corresponding stagnation pressure of small tail chamber inlet Mach number, unit pa；Dwx：Replaceable small tail chamber inlet diameter, unit mm；d4kpx：It removes
The supersonic speed engine throat diameter of experiment other than the test engine of engine export maximum flow, unit mm；
Wherein, true ring when the corresponding static pressure of replaceable small tail chamber inlet Mach number is with supersonic speed engine high-altitude flight
Border pressure is identical, the outlet of replaceable small tail chamber inlet Mach number corresponding stagnation pressure and the nozzle of supersonic speed engine
The corresponding stagnation pressure of Mach number is identical, and the nozzle exit Mach number of supersonic speed engine is more than 1, supersonic speed engine
Nozzle exit Mach number, the corresponding stagnation pressure of nozzle exit Mach number of supersonic speed engine, supersonic speed
True environmental pressure when engine high-altitude flight removes in specific heat ratio and engine testsand in the engine of all experiments
The engine throat diameter of engine other than the maximum engine of nozzle rate of discharge is solid for supersonic speed engine
Some known parameters, the parameter in above-mentioned equation group：Mwx, π (Mwx), Pwx, Pt5x, Dwx, d4kpx, it is institute in engine testsand
Have in the engine of experiment, the corresponding ginseng of supersonic speed engine in addition to the maximum engine of nozzle rate of discharge
Number.
Further, the length of the small tail room cylinder is Lwx, the length of the small tail room cylinder meets 500mm≤Lwx
≤600mm。
Further, the outlet of nozzle is L at a distance from the entrance section of tail room converging portionww, described
The outlet of nozzle meets 100mm≤L at a distance from the entrance section of tail room converging portionww≤150mm。
Further, the outlet of nozzle is 120mm at a distance from the entrance section of tail room converging portion.
Further, the outlet connection injector or vacuum tank of tail room expansion segment.
After the tail room of the present invention for engine testsand exhaust system is arranged, when engine export maximum flow
Test engine when being tested, the supersonic gas of nozzle outlet discharge flows into tail room converging portion, passes through
The tail cell structure of Laval nozzle shape dress is finally reduced to subsonic speed by a series of Shock Wave, and tail room converging portion enters a kind of horse raised north of the Grean Wall
Stagnation pressure P after the corresponding normal shock wave of conspicuous numbertw, the static pressure P in the corresponding altitude simulation cabin of tail room converging portion entrance Mach numberWAnd tail
The pressure ratio of roomMeet formula (11)-(13)；
When the test engine in addition to the test engine of engine export maximum flow is tested, engines tail
The supersonic gas of nozzle exit discharge flows into corresponding replaceable small tail room, passes through the tail room of class Laval nozzle shape
Structure, by a series of Shock Wave, after being finally reduced to the corresponding normal shock wave of the replaceable small tail chamber inlet Mach number of subsonic speed
Stagnation pressure Ptwx, the static pressure P in the corresponding altitude simulation cabin of replaceable small tail chamber inlet Mach numberWxAnd the pressure ratio of tail room
Meet formula (14)-(17)；
Wherein,For after the corresponding normal shock wave of replaceable small tail chamber inlet Mach number with the overall pressure tatio before normal shock wave.
Compared with prior art, the tail room of engine testsand exhaust system of the present invention, is sprayed by class Lavalle
The tail room analogue technique of tube shape, under serial Shock Wave, by the kinetic energy of nozzle, effectively stagnation is got off, and is more than
1 pressure ratio improves follow-up air-extractor and passively flows into a mouthful static pressure, reduces pressure ratio needed for follow-up air-extractor, and then reduce
The follow-up injector series of air-extractor or the volume of vacuum tank, reduce cost, meanwhile, replaceable small tail cell structure is set,
A kind of engine of nozzle size correspond to it is a kind of replacing small tail room, meet the need of sizes engine test
It asks.
Description of the drawings
The invention will be further described with reference to the accompanying drawings and detailed description.
Fig. 1 is the schematic diagram of the tail room of inventive engine test bay exhaust system.
Specific implementation mode
Referring to Fig. 1, a kind of tail room for engine testsand exhaust system, which is characterized in that the tail room includes solid
Fixed big tail room and replaceable small tail room 10, according to 3 exiting exhaust gas flow direction of nozzle, the big tail room of fixation includes
The tail room converging portion 4 being coaxially fixedly connected sequentially, the straight sections such as tail room 5 and tail room expansion segment 6, the replaceable small tail room 1 are arranged
It is fixedly and coaxially connected in tail room converging portion 4, and with tail room converging portion 4；Tail room converging portion 4, tail room etc. are straight
Section 5, tail room expansion segment 6 and replaceable small tail room 10 are hollow revolving body；Engine 2 with nozzle 3 and institute
It states tail room converging portion 4 to be arranged in altitude simulation cabin 1, tail room expansion segment 6 is arranged outside altitude simulation cabin 1, described to start
Machine 2 is supersonic speed engine.
Preferably, the equipment water jetting cooler for cooling down 3 exiting exhaust gas of nozzle is provided on fixed big tail room.
Preferably, the replaceable small tail room 10 includes the small tail room flange 8 being fixedly and coaxially connected and small tail room cylinder 9,
The small tail room cylinder 9 is arranged in tail room converging portion 4, and the small tail room flange 8 is received with the tail room is fixed at
The big tail room flange of fixation 7 for holding back 4 entrance of section is bolted to connection.
Preferably, a diameter of D of 4 entrance of tail room converging portionw, convergency αwr；The diameter of the straight sections 5 such as the tail room
Dwkp, length Lwkp；A diameter of D that tail room expansion segment 6 exportswc, angle of flare αwc；The Dw, Dwkp, LwkpMeet following
Equation group：
Lwkp=4Dwkp(7)；
In above-mentioned equation group：Mw：Tail room converging portion entrance Mach number；k：Specific heat ratio；π(Mw)：Tail room converging portion entrance Mach
The corresponding static pressure of number and stagnation pressure ratio；Pw：The corresponding static pressure of tail room converging portion entrance Mach number, unit pa；Pt5：It restrains tail room
The corresponding stagnation pressure of section entrance Mach number, unit pa；Dw：The diameter of tail room converging portion entrance, unit mm；d4kp：Engine larynx
Road diameter, unit mm；After the corresponding normal shock wave of tail room converging portion entrance Mach number with the overall pressure tatio before normal shock wave；q
(Mw)：The corresponding velocity coeffficient of tail room converging portion entrance Mach number；Dwkp：The diameter of the straight sections such as tail room, unit mm；Lwkp：Tail
The length of the straight sections such as room, unit mm；
Wherein, true environment when the corresponding static pressure of tail room converging portion entrance Mach number is with supersonic speed engine high-altitude flight
Pressure is identical, the outlet Mach of the corresponding stagnation pressure of tail room converging portion entrance Mach number and the nozzle of supersonic speed engine
The corresponding stagnation pressure of number is identical, and the nozzle exit Mach number of supersonic speed engine is more than 1, and supersonic speed engine starts
Tail nozzle exit Mach number, the corresponding stagnation pressure of nozzle exit Mach number of supersonic speed engine, supersonic speed are started
True environmental pressure when machine high-altitude flight, specific heat ratio and engine throat diameter are the intrinsic known ginseng of supersonic speed engine
It counts, the parameter in above-mentioned equation group：Mw, k, π (Mw), Pw, Pt5, Ww, d4kp,q(Mw), Dwkp, LwkpIt is engine testsand
In all experiments engine in, the corresponding parameter of the maximum engine of nozzle rate of discharge.
Preferably, the convergency meets：0 ＜ αwr≤12°；The angle of flare meets 0 ＜ αwc≤12°。
Preferably, a diameter of D of the replaceable small tail room 10wx, the DwxMeet following equations group：
In above-mentioned equation group：Mwx：Replaceable small tail chamber inlet Mach number；π(Mwx)：Replaceable small tail chamber inlet Mach number
Corresponding static pressure and stagnation pressure ratio；Pwx：The corresponding static pressure of replaceable small tail chamber inlet Mach number, unit pa；Pt5x：It is replaceable
The corresponding stagnation pressure of small tail chamber inlet Mach number, unit pa；Dwx：Replaceable small tail chamber inlet diameter, unit mm；d4kpx：It removes
The supersonic speed engine throat diameter of experiment other than the test engine of engine export maximum flow, unit mm；
Wherein, true ring when the corresponding static pressure of replaceable small tail chamber inlet Mach number is with supersonic speed engine high-altitude flight
Border pressure is identical, the outlet of replaceable small tail chamber inlet Mach number corresponding stagnation pressure and the nozzle of supersonic speed engine
The corresponding stagnation pressure of Mach number is identical, and the nozzle exit Mach number of supersonic speed engine is more than 1, supersonic speed engine
Nozzle exit Mach number, the corresponding stagnation pressure of nozzle exit Mach number of supersonic speed engine, supersonic speed
True environmental pressure when engine high-altitude flight removes in specific heat ratio and engine testsand in the engine of all experiments
The engine throat diameter of engine other than the maximum engine of nozzle rate of discharge is solid for supersonic speed engine
Some known parameters, the parameter in above-mentioned equation group：Mwx, π (Mwx), Pwx, Pt5x, Dwx, d4kpx, it is institute in engine testsand
Have in the engine of experiment, the corresponding ginseng of supersonic speed engine in addition to the maximum engine of nozzle rate of discharge
Number.
Preferably, the length of the small tail room cylinder 9 is Lwx, the length of the small tail room cylinder 9 meets 500mm≤Lwx
≤ 600mm, it is preferred that the length of the small tail room cylinder 9 is 560mm.
Preferably, the outlet of nozzle 3 is L at a distance from the entrance section of tail room converging portion 4ww, described
The outlet of nozzle 3 meets 100mm≤L at a distance from the entrance section of tail room converging portion 4ww≤150mm。
Preferably, the outlet of nozzle 3 is 120mm at a distance from the entrance section of tail room converging portion 4.
Preferably, the outlet connection injector or vacuum tank of tail room expansion segment.
After the tail room of the present invention for engine testsand exhaust system is arranged, when engine export maximum flow
Test engine when being tested, the supersonic gas of nozzle outlet discharge flows into tail room converging portion, passes through
The tail cell structure of Laval nozzle shape dress is finally reduced to subsonic speed by a series of Shock Wave, and tail room converging portion enters a kind of horse raised north of the Grean Wall
Stagnation pressure P after the corresponding normal shock wave of conspicuous numbertw, the static pressure P in the corresponding altitude simulation cabin of tail room converging portion entrance Mach numberWAnd tail
The pressure ratio of roomMeet formula (11)-(13)；
When the test engine in addition to the test engine of engine export maximum flow is tested, engines tail
The supersonic gas of nozzle exit discharge flows into corresponding replaceable small tail room, passes through the tail room of class Laval nozzle shape
Structure is finally reduced to subsonic speed by a series of Shock Wave, after the corresponding normal shock wave of replaceable small tail chamber inlet Mach number
Stagnation pressure Ptwx, the static pressure P of the corresponding stratochamber of replaceable small tail chamber inlet Mach numberWxAnd the pressure ratio of tail roomMeet
Formula (14)-(17)；
Wherein,For after the corresponding normal shock wave of replaceable small tail chamber inlet Mach number with the overall pressure tatio before normal shock wave.
Follow-up air-extractor is improved more than 1 pressure ratio and passively flows into a mouthful static pressure, reduces supercharging needed for follow-up air-extractor
Than, and then reduce the injector series of follow-up air-extractor or the volume of vacuum tank, reduce cost；Meanwhile being arranged and replacing
Small tail cell structure, a kind of engine of nozzle size correspond to it is a kind of replacing small tail room, meet sizes and start
The demand of machine experiment.
Finally illustrate, above example is only used to illustrate the technical scheme of the present invention and unrestricted, although with reference to compared with
Good embodiment describes the invention in detail, it will be understood by those of skill in the art that can be to the technology of the present invention
Scheme is modified and equivalent substitute, without departing from the objective and range of technical solution of the present invention, should all cover in the present invention
Right in.
Claims (8)
1. a kind of tail room for engine testsand exhaust system, which is characterized in that the tail room include fixed big tail room and
Replaceable small tail room (10), according to nozzle (3) exiting exhaust gas flow direction, the big tail room of fixation include coaxially according to
The secondary tail room converging portion (4) being fixedly connected, the straight sections such as tail room (5) and tail room expansion segment (6), the replaceable small tail room (10) set
It sets in tail room converging portion (4), and is fixedly and coaxially connected with tail room converging portion (4)；Tail room converging portion (4),
The straight sections such as tail room (5), tail room expansion segment (6) and replaceable small tail room (10) are hollow revolving body；With nozzle
(3) engine (2) and tail room converging portion (4) setting is interior in altitude simulation cabin (1), tail room expansion segment (6) setting
Altitude simulation cabin (1) outside, the engine (2) be supersonic speed engine；
The equipment water jetting cooler for cooling down nozzle (3) exiting exhaust gas is provided on fixed big tail room；
A diameter of D of the tail room converging portion (4) entrancew, convergency αwr；The diameter D of the straight sections such as described tail room (5)wkp, long
Degree is Lwkp；A diameter of D of tail room expansion segment (6) outletwc, angle of flare αwc；The Dw, Dwkp, LwkpMeet following equations
Group：
Lwkp=4Dwkp(7)；
In above-mentioned equation group：Mw：Tail room converging portion entrance Mach number；k：Specific heat ratio；π(Mw)：Tail room converging portion entrance Mach number pair
The static pressure answered and stagnation pressure ratio；Pw：The corresponding static pressure of tail room converging portion entrance Mach number, unit pa；Pt5：Tail room converging portion enters
The corresponding stagnation pressure of mouth Mach number, unit pa；Dw：The diameter of tail room converging portion entrance, unit mm；d4kp：Engine venturi is straight
Diameter, unit mm；After the corresponding normal shock wave of tail room converging portion entrance Mach number with the overall pressure tatio before normal shock wave；q(Mw)：Tail
The corresponding velocity coeffficient of room converging portion entrance Mach number；Dwkp：The diameter of the straight sections such as tail room, unit mm；Lwkp：The straight sections such as tail room
Length, unit mm；
Wherein, true environmental pressure when the corresponding static pressure of tail room converging portion entrance Mach number is with supersonic speed engine high-altitude flight
It is identical, the exit Mach number pair of the corresponding stagnation pressure of tail room converging portion entrance Mach number and the nozzle of supersonic speed engine
The stagnation pressure answered is identical, and the nozzle exit Mach number of supersonic speed engine is more than 1, the engines tail of supersonic speed engine
Nozzle exit Mach number, the corresponding stagnation pressure of nozzle exit Mach number of supersonic speed engine, supersonic speed engine are high
True environmental pressure when empty flight, specific heat ratio and engine throat diameter are the intrinsic known parameters of supersonic speed engine,
Parameter in above-mentioned equation group：Mw, k, π (Mw), Pw, Pt5, Ww, d4kp,q(Mw), Dwkp, LwkpIt is in engine testsand
In the engine of all experiments, the corresponding parameter of the maximum engine of nozzle rate of discharge.
2. the tail room according to claim 1 for engine testsand exhaust system, which is characterized in that described replaceable
Small tail room (10) includes the small tail room flange (8) being fixedly and coaxially connected and small tail room cylinder (9), and the small tail room cylinder (9) sets
It sets in the tail room converging portion (4), the small tail room flange (8) and is fixed at the tail room converging portion (4) entrance
Fixed big tail room flange (7) is bolted to connection.
3. the tail room according to claim 1 for engine testsand exhaust system, which is characterized in that the convergency
Meet：0 ＜ αwr≤12°；The angle of flare meets 0 ＜ αwc≤12°。
4. the tail room according to claim 1 or 3 for engine testsand exhaust system, which is characterized in that it is described can
Replace a diameter of D of small tail room (10)wx, the DwxMeet following equations group：
In above-mentioned equation group：Mwx：Replaceable small tail chamber inlet Mach number；π(Mwx)：Replaceable small tail chamber inlet Mach number is corresponding
Static pressure and stagnation pressure ratio；Pwx：The corresponding static pressure of replaceable small tail chamber inlet Mach number, unit pa；Pt5x：Replaceable small tail room
The corresponding stagnation pressure of entrance Mach number, unit pa；Dwx：Replaceable small tail chamber inlet diameter, unit mm；d4kpx：Engine tries
In ride in the engine of all experiments, engine in addition to the maximum engine of nozzle rate of discharge starts
Machine throat diameter, unit mm；
Wherein, true environment pressure when the corresponding static pressure of replaceable small tail chamber inlet Mach number is with supersonic speed engine high-altitude flight
Power is identical, the outlet Mach of replaceable small tail chamber inlet Mach number corresponding stagnation pressure and the nozzle of supersonic speed engine
The corresponding stagnation pressure of number is identical, and the nozzle exit Mach number of supersonic speed engine is more than 1, and supersonic speed engine starts
Tail nozzle exit Mach number, the corresponding stagnation pressure of nozzle exit Mach number of supersonic speed engine, supersonic speed are started
True environmental pressure when machine high-altitude flight, in specific heat ratio and engine testsand in the engine of all experiments, except starting
The engine throat diameter of engine other than the engine of tail nozzle exit maximum flow is that supersonic speed engine is intrinsic
Known parameters, the parameter in above-mentioned equation group：Mwx, π (Mwx), Pwx, Pt5x, Dwx, d4kpx, it is all examinations in engine testsand
In the engine tested, the corresponding parameter of supersonic speed engine in addition to the maximum engine of nozzle rate of discharge.
5. the tail room according to claim 2 for engine testsand exhaust system, which is characterized in that the small tail room
The length of cylinder (9) is Lwx, the length of the small tail room cylinder (9) meets 500mm≤Lwx≤600mm。
6. the tail room according to claim 1 for engine testsand exhaust system, which is characterized in that engines tail sprays
The outlet for managing (3) is L at a distance from the entrance section of tail room converging portion (4)ww, the outlet of the nozzle (3)
Section meets 100mm≤L at a distance from the entrance section of tail room converging portion (4)ww≤150mm。
7. the tail room according to claim 6 for engine testsand exhaust system, which is characterized in that engines tail sprays
The outlet for managing (3) is 120mm at a distance from the entrance section of tail room converging portion (4).
8. the tail room according to claim 1 for engine testsand exhaust system, which is characterized in that the tail room is expanded
Open the outlet connection injector or vacuum tank of section.
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| CN201610772826.9A CN106198030B (en) | 2016-08-30 | 2016-08-30 | Tail room for engine testsand exhaust system |
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|---|---|---|---|
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| CN109339983A (en) * | 2018-11-22 | 2019-02-15 | 内蒙航天动力机械测试所 | The verifying device of the virtual high mould experimental enviroment model of solid propellant rocket |
| CN112649202A (en) * | 2020-12-31 | 2021-04-13 | 北京航天三发高科技有限公司 | Cooling water system for engine test bed |
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