CN207080998U - Aero-engine ground direct-connect test air heating apparatus - Google Patents
Aero-engine ground direct-connect test air heating apparatus Download PDFInfo
- Publication number
- CN207080998U CN207080998U CN201720418139.7U CN201720418139U CN207080998U CN 207080998 U CN207080998 U CN 207080998U CN 201720418139 U CN201720418139 U CN 201720418139U CN 207080998 U CN207080998 U CN 207080998U
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- China
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- burn pot
- pipeline
- aero
- chovr body
- air inlet
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Abstract
Utility model discloses a kind of aero-engine ground direct-connect test air heating apparatus, including air inlet duct, pipeline, the first chovr body, flameholder, burn pot and the second chovr body；Air inlet duct is located at one end of whole heater, and air inlet duct one end is provided with air intake, and the other end is connected with pipeline；The other end of pipeline is connected by the first chovr body with burn pot；Flameholder is located in burn pot；The burn pot other end is connected with the second chovr body, and the other end is provided with gas outlet；Pipeline is radially provided with hydrogen inlet close to air intake pipe end, and lighting-up tuyere is radially provided with close to the first switching body end；Burn pot intermediate radial is provided with oxygen intake, and pressure sensor interface and temperature sensor interface are radially provided with close to the second switching body end；Pressure sensor and temperature sensor are separately installed with pressure sensor interface and temperature sensor interface；The utility model is simple in construction, and stability is good, close to engine practical working situation.
Description
Technical field
The utility model belongs to air heating apparatus field, and in particular to a kind of aero-engine ground direct-connect test is empty
Gas heater.
Background technology
Direct-connect test technology is a very crucial technology in aero-engine research.Aero-engine is direct-connected
Experimental technique is that aeroengine combustor buring room and experimental rig are directly connected to by pipeline or simulation venturi on ground,
By the regulation to experimental rig, combustion chamber inlet air flow parameter and exhaust parameter is artificially set to join with air-flow during practical flight
Number is identical, and the inlet air flow parameter of combustion chamber includes flow, stagnation temperature, stagnation pressure and Mach number, wherein the Mach number of inlet air flow and
Structure is relevant, and in the case where ensure that the precondition of inlet flow rate, stagnation temperature and stagnation pressure, one is kept when import section and practical flight
Cause, the free stream Mach number with regard to strict guarantee.
The aero-engine ground direct-connect test air heating apparatus of prior art uses electrically heated heat absorption type mostly
Heater, such as in document Amnon Netzer, Alon Gany.Burning and Flameholding
Characteristics of a Miniature Solid Fuel Ramjet Combustor[R].AIAA88-3044,
The electric heater mentioned in 1988., this air heater heated perimeter is limited, only up to reach 800K, and power consumption
Greatly, research cost is high.Also have using fuel combustion in engine direct-connect test to heat the device of air, such as in document Lee
It is small flat, Ge Lihu, application study [J] the rocket propulsions of Luan Xi booth heaters in punching engine experimental technique, 2007,
33(3):The direct-connected testing stand of punching engine mentioned in 14-19., but often build is huge for these devices, it is complicated, it is required
It is large-minded, cause research cost very high.
The content of the invention
The technical problem that the utility model solves is that providing a kind of aero-engine ground direct-connect test air adds
Thermal, to solve the problems, such as that existing heater structure is complicated, experimentation cost is high.
The technical solution for realizing the utility model purpose is：
A kind of heating trial assembly of aero-engine ground direct-connect test air is put, including air inlet duct, pipeline, first turn
Junctor, flameholder, burn pot and the second chovr body；
The air inlet duct is located at one end of whole heater, and air inlet duct one end is provided with air intake；Air
The inlet tube other end is connected with pipeline；The other end of the pipeline is connected by the first chovr body with burn pot；Flameholder
In burn pot, and between flameholder is located in the first chovr body and burn pot, the conical end direction of flameholder
Pipeline side；The burn pot other end is connected with the second chovr body；The other end of second chovr body is provided with gas outlet；
The pipeline is radially provided with hydrogen inlet close to air intake pipe end；Pipeline is radially provided with lighting-up tuyere close to the first switching body end；
The burn pot intermediate radial is provided with oxygen intake；Burn pot close to second switching body end be radially provided with pressure sensor interface and
Temperature sensor interface；Pressure sensor and TEMP are separately installed with pressure sensor interface and temperature sensor interface
Device.
The utility model compared with prior art, its remarkable advantage：
(1) heated using H2 and air burning so that into the cleaning gas of engine chamber, quality better, burning
The middle part of tank 5 addition oxygen, more can be close to engine practical working situation；
(2) combustion stability is good, and heated perimeter is wide (600K~1500K), and aero-engine can be met in speed of incoming flow 2
Simulated test between~4.5Ma；
(3) simple in construction, small volume, research cost is low, and security and stability is high.
The utility model is described in further detail below in conjunction with the accompanying drawings.
Brief description of the drawings
Fig. 1 is aero-engine ground direct-connect test air heating apparatus cross section structure diagram.
Fig. 2 is air inlet duct front view.
Fig. 3 is flameholder sectional view.
Fig. 4 is that burn pot is located at sectional view at oxygen intake.
Embodiment
In order to illustrate the technical solution of the utility model and technical purpose, below in conjunction with the accompanying drawings and specific embodiment is to this reality
It is described further with new.
With reference to Fig. 1, Fig. 3, a kind of aero-engine ground direct-connect test air heating apparatus of the present utility model, including
Air inlet duct 1, pipeline 2, the first chovr body 3, flameholder 4, the chovr body 6 of burn pot 5 and second；
The air inlet duct 1 is located at one end of whole heater, and air inlet duct 1 is the cylinder that both ends are provided with through hole
Shape cavity body structure, the one end of air inlet duct 1 is provided with air intake 11, for connecting external air pressure tank；Air inlet duct 1 is another
One end is connected with pipeline 2；The other end of the pipeline 2 is connected by the first chovr body 3 with burn pot 5；Flameholder 4 is located at
In burn pot 5, and between flameholder 4 is located in the first chovr body 3 and burn pot 5, the conical end direction of flameholder 4
The side of pipeline 2；The other end of burn pot 5 is connected with the second chovr body 6；The other end of second chovr body 6 is provided with combustion gas
Outlet 61；The pipeline 2 position at the end 1/3 of air inlet duct 1, is radially provided with hydrogen inlet 21, for connecting external hydrogen
Atmospheric pressure tank；Pipeline 2 is radially provided with lighting-up tuyere 22 close to the end of the first chovr body 3, and gas is lighted for spark plug point；The burning
The intermediate radial of tank 5 is provided with oxygen intake 51, for connecting external oxygen pressurized tank；Burn pot 5 is close to the end of the second chovr body 6 radial direction
Provided with pressure sensor interface 52 and temperature sensor interface 53；Divide on pressure sensor interface 52 and temperature sensor interface 53
Pressure sensor and temperature sensor are not installed, the gas pressure and temperature for being respectively used to test when burning in burn pot 5 become
Change, so as to be adjusted into outside aero-engine speed of incoming flow and temperature of incoming flow.
Further, first chovr body 3 is one end cone, the turriform cavity knot for the composition that the other end is cylinder
Structure；Conical end is connected with pipeline 2, and cylindrical end is connected provided with external screw thread with the internal thread of burn pot 5 by screw thread, in burn pot 5 with
The connected end of first chovr body 3 is provided with a circle step, and flameholder 4 is caught on the step of burn pot 5 by the first chovr body 3.
With reference to Fig. 2, further, the quantity of air intake 11 is that n (n >=1) is evenly distributed on air inlet duct 1
End face axial one week；Preferably, n is 4, can connect 4 air pressure containers simultaneously, is easy to ensure the steady of supply air pressure
It is qualitative.
The coning angle of the cone of the flameholder 4 between 30 °~60 °, be advantageous to burning gases stablize it is excessive
To combustion chamber.
With reference to Fig. 4, the quantity of oxygen intake 51 is m (m >=1), is evenly distributed on one week of burn pot 5；Oxygen enters
Mouth 51 is The more the better, is easy to oxygen uniformly to be mixed with the gas after preceding end burning.
In aero-engine ground experiment, flow, stagnation temperature, stagnation pressure and the horse of strict guarantee test model inlet air
Conspicuous number, wherein simulation stagnation temperature is a very crucial and important link.The pressure-controlled empty that the present embodiment passes through outside tracheae
Gas and H2 mixed proportion and flow simultaneously and then control the stagnation temperature in burn pot 5.Air is tested from the air inlet of air inlet 11
Inlet tube 1, air and H2 are mixed in pipeline 2, and after being lighted a fire in pipeline 2 by lighting-up tuyere 22, burning gases are steady along flame
The center cone for determining device 4 enters in burn pot 5.Hydrogen is sufficiently mixed in the presence of flameholder 4 with air, and in burn pot
Stable burning in 5, so as to improve incoming experiment air stagnation temperature.In the middle part of burn pot 5 addition oxygen, disappeared with supplementing in mixed gas
The oxygen consumed so that oxygen content is consistent with oxygen content during its flight in the air in ground experiment engine Incoming gas.
Measure the temperature and pressure of gas in burn pot 5 respectively by temperature sensor and pressure sensor, compared with theoretical value,
And then adjust air and H2 mixed proportions and flow.Then the high-temperature gas by heater processing passes through gas outlet 61
Spray and obtain required high stagnation temperature gas.
The utility model is heated using H2 and air burning so that into the cleaning gas of engine chamber, quality better,
Oxygen is added at the middle part of burn pot 5, to supplement the oxygen consumed in mixed gas so that ground experiment engine Incoming gas
Middle oxygen content is consistent with oxygen content during its flight in the air, more can be close to engine practical working situation；Passed by temperature
Sensor and pressure sensor measure the temperature and pressure of gas in burn pot 5 respectively, adjust heated perimeter (600K~1500K),
Simulated test of the aero-engine between 2~4.5Ma of speed of incoming flow can be met；The utility model is simple in construction, it is not necessary to cold
But device, research cost is low, and security and stability is high.
Although the utility model is disclosed above with preferred embodiment, so it is not limited to the utility model.This reality
With new those of ordinary skill in the art, do not departing from spirit and scope of the present utility model, it is each when that can make
The change and retouching of kind.Therefore, the scope of protection of the utility model is worked as and is defined depending on those as defined in claim.
Claims (5)
- A kind of 1. aero-engine ground direct-connect test air heating apparatus, it is characterised in that including air inlet duct (1), Pipeline (2), the first chovr body (3), flameholder (4), burn pot (5) and the second chovr body (6)；The air inlet duct (1) is located at one end of whole heater, and air inlet duct (1) one end is provided with air intake (11)；Air inlet duct (1) other end is connected with pipeline (2)；The other end of the pipeline (2) by the first chovr body (3) with Burn pot (5) is connected；Flameholder (4) is located in burn pot (5), and flameholder (4) be located at the first chovr body (3) and Between in burn pot (5), the conical end of flameholder (4) is towards pipeline (2) side；Burn pot (5) other end and Two chovr bodies (6) are connected；The other end of second chovr body (6) is provided with gas outlet (61)；The pipeline (2) is close to air Inlet tube (1) end is radially provided with hydrogen inlet (21)；Pipeline (2) is radially provided with lighting-up tuyere (22) close to the first chovr body (3) end； Burn pot (5) intermediate radial is provided with oxygen intake (51)；Burn pot (5) is radially provided with pressure close to the second chovr body (6) end Force snesor interface (52) and temperature sensor interface (53)；On pressure sensor interface (52) and temperature sensor interface (53) It is separately installed with pressure sensor and temperature sensor.
- 2. aero-engine ground direct-connect test air heating apparatus as claimed in claim 1, it is characterised in that the sky Gas entrance (11) quantity is n, and n >=1, air intake (11) is evenly distributed on air inlet duct (1) end face axial one week.
- 3. aero-engine ground direct-connect test air heating apparatus as claimed in claim 2, it is characterised in that the sky Gas entrance (11) quantity n=4.
- 4. aero-engine ground direct-connect test air heating apparatus as claimed in claim 1, it is characterised in that the fire The coning angle of the cone of flame stabilizer (4) is between 30 °~60 °.
- 5. aero-engine ground direct-connect test air heating apparatus as claimed in claim 1, it is characterised in that the oxygen Gas entrance (51) quantity is m, and m >=1, oxygen intake (51) is evenly distributed on one week of burn pot (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720418139.7U CN207080998U (en) | 2017-04-20 | 2017-04-20 | Aero-engine ground direct-connect test air heating apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720418139.7U CN207080998U (en) | 2017-04-20 | 2017-04-20 | Aero-engine ground direct-connect test air heating apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207080998U true CN207080998U (en) | 2018-03-09 |
Family
ID=61436173
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720418139.7U Expired - Fee Related CN207080998U (en) | 2017-04-20 | 2017-04-20 | Aero-engine ground direct-connect test air heating apparatus |
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| CN (1) | CN207080998U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143849A (en) * | 2017-04-20 | 2017-09-08 | 南京理工大学 | Aero-engine ground direct-connect test air heating apparatus |
-
2017
- 2017-04-20 CN CN201720418139.7U patent/CN207080998U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143849A (en) * | 2017-04-20 | 2017-09-08 | 南京理工大学 | Aero-engine ground direct-connect test air heating apparatus |
| CN107143849B (en) * | 2017-04-20 | 2023-04-11 | 南京理工大学 | Ground direct-connected test air heating device for aero-engine |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180309 Termination date: 20200420 |
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| CF01 | Termination of patent right due to non-payment of annual fee |