CN108132149A - A kind of aero-engine inlet distortion wire examination method - Google Patents
A kind of aero-engine inlet distortion wire examination method Download PDFInfo
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- CN108132149A CN108132149A CN201711220142.9A CN201711220142A CN108132149A CN 108132149 A CN108132149 A CN 108132149A CN 201711220142 A CN201711220142 A CN 201711220142A CN 108132149 A CN108132149 A CN 108132149A
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- steam
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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
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A kind of aero-engine inlet distortion wire examination method, specially air intake duct is the full-scale air intake duct that engine is examined to be equipped with aircraft, it is fixed by the bracket in test bay moving frame, engine is identical with air intake duct faying face diameter, directly dock, engine and moving frame save pin by installation and fix, and moving frame is connected with quiet frame by sliding rail；A set of boiler plant is set, for generating high-temperature steam, for the water in water softener by softening by water pipe to feed pump, softened water is pumped into steam boiler by feed pump by water pipe, the steam of steam boiler is transported to steam storage tank by water pipe, and the steam of steam storage tank removes experimental rig by water pipe.The yield of high-temperature steam is determined by test engine inlet temperature conditions, intake air flow, set steam vapour amount.Advantages of the present invention：Higher consistency can be kept with true environment, make result of the test credible.To checking that stability, reliability that engine works under big Mach number are of great significance.
Description
Technical field
The present invention relates to Aero Engine Testing and technical field of measurement and test, a kind of more particularly to aero-engine air inlet is abnormal
Become wire examination method.
Background technology
Need to test or examine the inlet distortion ability of engine in Aero-engine Development, to verify engine
Whether the reliability that at different conditions uses is met.
When aircraft carries out high Mach flight in the air, engine intake atmospheric temperature steeply rises, and airplane intake exists
Sucking containing a large amount of clouds and mists air event in, become containing high-temperature steam hot-air, these contain high-temperature steam hot-air into
Enter engine runner, influence the job stability of engine.
The method generally use of traditional examination engine charge distortion ability is to gulp down cigarette, gulp down water, air intake duct plate etc.
Method.These conventional methods cannot true environment that effectively simulated engine works in the air, examine the anti-inlet distortion of engine
There are certain deviations for ability and truth.By taking air intake duct inlet baffle method as an example, this test method can only simulate into
Air flue turbulent flow situation, it is impossible to the effectively reflection true inlet air situation of engine.
Invention content
The purpose of the present invention is swallowing high-temperature steam by engine, simulation aero-engine under the high-speed case of high-altitude,
Into temperature rise it is drastically raised under the conditions of, examine the anti-inlet distortion ability of engine, stability margin has provided a kind of aviation hair
Motivation inlet distortion wire examination method.
The present invention provides a kind of aero-engine inlet distortion wire examination methods, it is characterised in that：The aeroplane engine
Machine inlet distortion wire examination method, specially air intake duct are the full-scale air intake duct that engine is examined to be equipped with aircraft, are consolidated by stent
It is scheduled in test bay moving frame, engine is identical with air intake duct faying face diameter, directly docks, and engine and moving frame are saved by installing
Pin is fixed, and moving frame is connected with quiet frame by sliding rail.
A set of boiler plant is set, for generating high-temperature steam.Water in water softener passes through water pipe to feedwater by softening
Softened water is pumped into steam boiler by pump, feed pump by water pipe, and the steam of steam boiler is transported to steam storage tank by water pipe,
The steam of steam storage tank removes experimental rig by water pipe.The yield of high-temperature steam by test engine inlet temperature conditions,
Intake air flow, set steam vapour amount determine；During experiment, high-temperature steam is transported to test-bed Fighter Inlet
Place, according to different engine speed requirement and charge flow rate requirement, the steam conveying continued for some time will to meet experiment
It asks.
Step 1：Engine height, speed calculating are carried out, aerial air inflow is simulated and temperature rises item
Part proposes steam demand amount.
Step 2：It purchases steam boiler to examine for testing, boiler generates steam index and meets the requirement of steam demand amount.
Step 3：Test Rig repacking is carried out, installation actual airplane air intake duct, arrangement boiler to inlet mouth can be met
Steam conveying pipeline.
Step 4：Experiment examination is carried out, engine is operated in into maximum rating or design examination state, by the steaming of setting
Vapour amount is transported to inlet mouth, requires examination engine stabilization according to flying condition, enrolls test parameters.
Step 5：Calculating analysis is carried out to the experiment result of appraisal, assesses the anti-inlet distortion ability of engine.
Advantages of the present invention：
This invention method can keep higher consistency with true environment, by simulating full-scale condition, tie experiment
Fruit is credible.The test method of high-temperature steam sucking air intake duct anti-inlet distortion ability can effectively assess engine,
To checking that stability, reliability that engine works under big Mach number are of great significance.The engine charge distorts at present
Wire examination method has been applied on two kinds of engines, and assessment method is rationally effective, by multiple certification test, has reached expected effect
Fruit obtains good technical benefits and safety benefit.
Description of the drawings
Below in conjunction with the accompanying drawings and embodiment the present invention is described in further detail：
Fig. 1 is engine rig test schematic diagram；
Fig. 2 is high-temperature steam generator equipment schematic diagram；
In figure, 1 is engine, and 2 be air intake duct, and 3 be moving frame, and 4 be quiet frame, and 5 be water softener, and 6 be feed pump, and 7 be steam
Boiler, 8 be steam storage tank.
Specific embodiment
Embodiment 1
The present invention provides a kind of aero-engine inlet distortion wire examination methods, it is characterised in that：The aeroplane engine
Machine inlet distortion wire examination method, specially air intake duct are the full-scale air intake duct that engine is examined to be equipped with aircraft, are consolidated by stent
It is scheduled in test bay moving frame, engine is identical with air intake duct faying face diameter, directly docks, and engine and moving frame are saved by installing
Pin is fixed, and moving frame is connected with quiet frame by sliding rail.
A set of boiler plant is set, for generating high-temperature steam, is seen.Water in water softener is by softening by water pipe to giving
Softened water is pumped into steam boiler by water pump, feed pump by water pipe, and the steam of steam boiler is transported to steam by water pipe and stores
Tank, the steam of steam storage tank remove experimental rig by water pipe.The yield of high-temperature steam is by test engine inlet temperature item
Part, intake air flow, set steam vapour amount determine；During experiment, by high-temperature steam be transported to test-bed air intake duct into
At mouthful, according to different engine speed requirement and charge flow rate requirement, the steam conveying continued for some time, to meet experiment
It is required that.
Step 1：Engine height, speed calculating are carried out, aerial air inflow is simulated and temperature rises item
Part proposes steam demand amount.
Step 2：It purchases steam boiler to examine for testing, boiler generates steam index and meets the requirement of steam demand amount.
Step 3：Test Rig repacking is carried out, installation actual airplane air intake duct, arrangement boiler to inlet mouth can be met
Steam conveying pipeline.
Step 4：Experiment examination is carried out, engine is operated in into maximum rating or design examination state, by the steaming of setting
Vapour amount is transported to inlet mouth, requires examination engine stabilization according to flying condition, enrolls test parameters.
Step 5：Calculating analysis is carried out to the experiment result of appraisal, assesses the anti-inlet distortion ability of engine.
Embodiment 2
The present invention provides a kind of aero-engine inlet distortion wire examination methods, it is characterised in that：The aeroplane engine
Machine inlet distortion wire examination method, specially air intake duct are the full-scale air intake duct that engine is examined to be equipped with aircraft, are consolidated by stent
It is scheduled in test bay moving frame, engine is identical with air intake duct faying face diameter, directly docks, and engine and moving frame are saved by installing
Pin is fixed, and moving frame is connected with quiet frame by sliding rail.
A set of boiler plant is set, for generating high-temperature steam, is seen.Water in water softener is by softening by water pipe to giving
Softened water is pumped into steam boiler by water pump, feed pump by water pipe, and the steam of steam boiler is transported to steam by water pipe and stores
Tank, the steam of steam storage tank remove experimental rig by water pipe.The yield of high-temperature steam is by test engine inlet temperature item
Part, intake air flow, set steam vapour amount determine；During experiment, by high-temperature steam be transported to test-bed air intake duct into
At mouthful, according to different engine speed requirement and charge flow rate requirement, the steam conveying continued for some time, to meet experiment
It is required that.
Claims (2)
1. a kind of aero-engine inlet distortion wire examination method, it is characterised in that：The aero-engine inlet distortion examination
Method, specially air intake duct are the full-scale air intake duct that engine is examined to be equipped with aircraft, are fixed by the bracket in test bay moving frame
On, engine is identical with air intake duct faying face diameter, directly docks, and engine and moving frame save pin by installation and fix, moving frame
It is connected with quiet frame by sliding rail；
A set of boiler plant is set, for generating high-temperature steam, water in water softener by softening by water pipe to feed pump, give
Softened water is pumped into steam boiler by water pump by water pipe, and the steam of steam boiler is transported to steam storage tank, steam by water pipe
The steam of storage tank removes experimental rig by water pipe.The yield of high-temperature steam is by test engine inlet temperature conditions, import
Air mass flow, set steam vapour amount determine；During experiment, high-temperature steam is transported at test-bed Fighter Inlet, is pressed
According to different engine speed requirement and charge flow rate requirement, the steam conveying continued for some time, to meet test requirements document.
2. aero-engine inlet distortion wire examination method described in accordance with the claim 1, it is characterised in that：The aeroplane engine
Machine inlet distortion wire examination method, including step in detail below：
Step 1：Engine height, speed calculating are carried out, aerial air inflow and temperature condition is simulated, proposes steam demand amount.
Step 2：It purchases steam boiler to examine for testing, boiler generates steam index and meets the requirement of steam demand amount.
Step 3：Test Rig repacking is carried out, installation actual airplane air intake duct, the steaming of arrangement boiler to inlet mouth can be met
Vapour transfer pipeline.
Step 4：Experiment examination is carried out, engine is operated in into maximum rating or design examination state, by the quantity of steam of setting
Inlet mouth is transported to, examination engine stabilization is required according to flying condition, enrolls test parameters.
Step 5：Calculating analysis is carried out to the experiment result of appraisal, assesses the anti-inlet distortion ability of engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711220142.9A CN108132149A (en) | 2017-11-29 | 2017-11-29 | A kind of aero-engine inlet distortion wire examination method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711220142.9A CN108132149A (en) | 2017-11-29 | 2017-11-29 | A kind of aero-engine inlet distortion wire examination method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108132149A true CN108132149A (en) | 2018-06-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711220142.9A Pending CN108132149A (en) | 2017-11-29 | 2017-11-29 | A kind of aero-engine inlet distortion wire examination method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112240831A (en) * | 2020-10-15 | 2021-01-19 | 厦门大学 | Design method of aero-engine intake temperature distortion generator |
Citations (7)
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| CN202054642U (en) * | 2011-03-21 | 2011-11-30 | 上海耐福金属制造有限公司 | Water treatment system |
| CN202305215U (en) * | 2011-10-14 | 2012-07-04 | 桑增产 | System for testing pressure distortion characteristic of air compressor of turbine shaft engine |
| CN102680238A (en) * | 2012-05-29 | 2012-09-19 | 西北工业大学 | Non-contact engine thrust testing method and device |
| CN202793796U (en) * | 2012-09-28 | 2013-03-13 | 中航商用航空发动机有限责任公司 | Actuating device of intake pressure distortion baffle and intake pressure distortion test equipment |
| CN103234761A (en) * | 2013-04-12 | 2013-08-07 | 北京航空航天大学 | Mobile test platform for low-thrust rocket engines |
| CN103471852A (en) * | 2013-09-27 | 2013-12-25 | 北京动力机械研究所 | Flow distortion simulation device |
| CN104359096A (en) * | 2014-11-07 | 2015-02-18 | 苏州迈创信息技术有限公司 | Electric steam generator and steam generator control system |
-
2017
- 2017-11-29 CN CN201711220142.9A patent/CN108132149A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202054642U (en) * | 2011-03-21 | 2011-11-30 | 上海耐福金属制造有限公司 | Water treatment system |
| CN202305215U (en) * | 2011-10-14 | 2012-07-04 | 桑增产 | System for testing pressure distortion characteristic of air compressor of turbine shaft engine |
| CN102680238A (en) * | 2012-05-29 | 2012-09-19 | 西北工业大学 | Non-contact engine thrust testing method and device |
| CN202793796U (en) * | 2012-09-28 | 2013-03-13 | 中航商用航空发动机有限责任公司 | Actuating device of intake pressure distortion baffle and intake pressure distortion test equipment |
| CN103234761A (en) * | 2013-04-12 | 2013-08-07 | 北京航空航天大学 | Mobile test platform for low-thrust rocket engines |
| CN103471852A (en) * | 2013-09-27 | 2013-12-25 | 北京动力机械研究所 | Flow distortion simulation device |
| CN104359096A (en) * | 2014-11-07 | 2015-02-18 | 苏州迈创信息技术有限公司 | Electric steam generator and steam generator control system |
Non-Patent Citations (1)
| Title |
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| 尤延铖 等: ""航空发动机进气温度畸变研究综述"", 《南京航空航天大学学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112240831A (en) * | 2020-10-15 | 2021-01-19 | 厦门大学 | Design method of aero-engine intake temperature distortion generator |
| CN112240831B (en) * | 2020-10-15 | 2021-06-29 | 厦门大学 | Design method of aero-engine intake temperature distortion generator |
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Application publication date: 20180608 |