CN106404406A - Aero-engine environment simulation device - Google Patents
Aero-engine environment simulation device Download PDFInfo
- Publication number
- CN106404406A CN106404406A CN201610901059.7A CN201610901059A CN106404406A CN 106404406 A CN106404406 A CN 106404406A CN 201610901059 A CN201610901059 A CN 201610901059A CN 106404406 A CN106404406 A CN 106404406A
- Authority
- CN
- China
- Prior art keywords
- aero
- engine
- motor
- engine environment
- whirligig
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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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
Abstract
The present invention discloses an aero-engine environment simulation device. The device comprises a blade (1), a rotation device (3), a fuel nozzle (4), a bearing pedestal (5), a coupling (6), a transmission (7), a motor (8), a controller (9) and a rack (10). The rotation device (3), the bearing pedestal (5), the transmission (7), the motor (8) and the controller (9) are arranged on the rack (10) in order; the transmission (7) and the motor (8) are connected with the coupling (6) through the rotation device (3); and the fuel nozzle (4) is arranged right above of the rotation device (3). The aero-engine environment simulation device is unique in design and novel in structure, can really simulate the environmental factors of the engine such as high temperature, high voltage, high speed and multi-medium corrosion, can allow samples to obtain high rotation speed, and can establish the real usage condition of an engine heating part; and moreover the device is simple in structure, convenient to operation and high in practicability.
Description
Technical field
The present invention relates to engine components thermal performance test technical field is and in particular to a kind of aero-engine environmental simulation
Device.
Background technology
Heat etching frequently results in engine thermal end pieces and initial failure occurs, and is the normal huge safety run of aero-engine
Hidden danger.Worldwide, civil aviaton's High Pressure Turbine Rotor corrosion of blade has led to 42 leaf destruction faults, wherein causes 7
Sky stops accident.So, accurately examine the heat etching performance of engine thermal component materials in laboratory environment, be to ensure that aero-engine
One basic task of reliable and stable operation.Accurately examine the heat etching performance of engine thermal component materials in laboratory environments,
High temperature (more than 1500 DEG C), high pressure, at a high speed (1000m/s) and the multimedium corrosion being equal to engine actual condition must be obtained
Many environmental factors such as (NaCl, Na2SO4).At present, domestic heat etching test common method mainly has crucible molten-salt growth method, applies salt
Method, salt drench method and melten salt electriochemistry method etc., and conventional test temperature is mainly between 750-900 DEG C.These tests either temperature
, all there is larger gap with engine actual condition in degree or ambiance aspect.Certainly obtained test result also with
The actually used situation of engine thermal part has larger gap.So, domestic at present conventional heat etching test result is to hot portion
The life-span of part can only provide a reference value it is impossible to accurately be estimated to it.
Content of the invention
For problems of the prior art, the invention provides a kind of aero-engine environment simulator, solve
The problems that existing method of testing exists.
The present invention adopts the following technical scheme that：
A kind of aero-engine environment simulator, including blade, whirligig, burner, bearing block, shaft coupling, change
Fast device, motor, controller and stand it is characterised in that：Described whirligig, bearing block, speed changer, motor, controller are successively
Arrangement is arranged on stand；Described speed changer, motor are connected by shaft coupling with described whirligig；Described burner is arranged on
Directly over whirligig.
Further, described whirligig is connected on stand by bearing block.
Further, described blade exterior is provided with protective cover.
With respect to prior art, it is an advantage of the current invention that：
Present invention design is unique, structure is novel, and described aero-engine environment simulator adopts commercial aviation kerosene to make
For fuel, not only can truly simulated engine high temperature (more than 1500 DEG C), high pressure, at a high speed (1000m/s) and multimedium corrode
Many environmental factors such as (NaCl, Na2SO4), can also make sample obtain high rotating speed (10,000 revs/min), in laboratory
The actually used operating mode of an engine thermal part is set up under environment.In brief, this platform can enter to engine thermal part
The detection of the performances such as row oxidation, high temperature corrosion, heat fatigue and erosion.
Brief description
Fig. 1 is the structural representation of the present invention.
Specific embodiment
For making the purpose of the present invention, technical scheme and effect clearer, clear and definite, below to the present invention further specifically
Bright：
A kind of aero-engine environment simulator as shown in Figure 1, including blade 1, whirligig 3, burner 4, axle
Bearing 5, shaft coupling 6, speed changer 7, motor 8, controller 9 and stand 10 it is characterised in that：Described whirligig 3, bearing block 5,
Speed changer 7, motor 8, controller 9 are arranged successively and are arranged on described stand 10；Described speed changer 7, motor 8 and described rotating dress
Put 3 to connect by shaft coupling 6；Described burner 4 is arranged on directly over whirligig 3.Described whirligig 3 passes through bearing block 5
It is connected on stand 10；It is provided with protective cover 2 outside described blade 1.
Its operation principle is as follows：Described motor 8, speed changer 7 start, and device 3 are rotated by shaft coupling 6 and rotate, make
Blade obtains the high rotating speed needing；After blade slow-roll stabilization, burner 4 starts, and obtains high temperature, the fuel gas flow of high speed, leads to
Cross burner 4 and be ejected into blade 1 surface, complete blade Work condition analogue.
In sum, present invention design is unique, structure is novel, not only can truly simulated engine high temperature, high pressure, at a high speed
With many environmental factors such as multimedium corrosion, sample can also be made to obtain high rotating speed, set up one in laboratory environments
The actually used operating mode of engine thermal part.This device has structure simply, easy to operate, the advantages of practical.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, Er Qie
In the case of the spirit or essential attributes of the present invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, embodiment all should be regarded as exemplary, and be nonrestrictive, the scope of the present invention is by appended power
Profit requires rather than described above limits, it is intended that all in the implication and scope of the equivalency of claim by falling
Change is included in the present invention.Any reference in claim should not be considered as limiting involved claim.
Moreover, it will be appreciated that although this specification is been described by according to embodiment, not each embodiment only wraps
Containing an independent technical scheme, only for clarity, those skilled in the art should for this narrating mode of specification
Using specification as an entirety, the technical scheme in each embodiment can also form those skilled in the art through appropriately combined
Understandable other embodiment.
Claims (3)
1. a kind of aero-engine environment simulator, including blade (1), whirligig (3), burner (4), bearing block (5),
Shaft coupling (6), speed changer (7), motor (8), controller (9) and stand (10) it is characterised in that：Described whirligig (3), axle
Bearing (5), speed changer (7), motor (8), controller (9) are arranged successively and are arranged on stand (10)；Described speed changer (7), electricity
Machine (8) is connected by shaft coupling (6) with described whirligig (3)；Described burner (4) is arranged on directly over whirligig (3).
2. a kind of aero-engine environment simulator according to claim 1 it is characterised in that：Described whirligig
(3) it is connected on stand (10) by bearing block (5).
3. a kind of aero-engine environment simulator according to claim 1 it is characterised in that：It is characterized in that：Institute
State and be provided with protective cover (2) outside blade (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610901059.7A CN106404406A (en) | 2016-10-17 | 2016-10-17 | Aero-engine environment simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610901059.7A CN106404406A (en) | 2016-10-17 | 2016-10-17 | Aero-engine environment simulation device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106404406A true CN106404406A (en) | 2017-02-15 |
Family
ID=58011778
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610901059.7A Pending CN106404406A (en) | 2016-10-17 | 2016-10-17 | Aero-engine environment simulation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106404406A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307599A (en) * | 2018-10-15 | 2019-02-05 | 北京矿冶科技集团有限公司 | Test hot environment simulation system, abradable testing machine and temprature control method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1777507A2 (en) * | 2005-10-19 | 2007-04-25 | Rolls-Royce plc | Gas turbine engine simulator |
| CN101231209A (en) * | 2008-02-02 | 2008-07-30 | 长沙理工大学 | Load-dependent vibration reduction experimental system with damping structure blade |
| CN103091238A (en) * | 2013-01-10 | 2013-05-08 | 湘潭大学 | Test platform with integrated dynamic and static service environments for thermal-barrier-coated turbine blades |
| CN103630314A (en) * | 2013-11-25 | 2014-03-12 | 苏州东菱振动试验仪器有限公司 | Blade high on-line air flow excitation system and test method |
| CN204720053U (en) * | 2015-05-18 | 2015-10-21 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of infrared measurement of temperature simulation device |
| CN205262756U (en) * | 2015-12-25 | 2016-05-25 | 中北大学 | High nip drum stream of engine test device that admits air |
-
2016
- 2016-10-17 CN CN201610901059.7A patent/CN106404406A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1777507A2 (en) * | 2005-10-19 | 2007-04-25 | Rolls-Royce plc | Gas turbine engine simulator |
| CN101231209A (en) * | 2008-02-02 | 2008-07-30 | 长沙理工大学 | Load-dependent vibration reduction experimental system with damping structure blade |
| CN103091238A (en) * | 2013-01-10 | 2013-05-08 | 湘潭大学 | Test platform with integrated dynamic and static service environments for thermal-barrier-coated turbine blades |
| CN103630314A (en) * | 2013-11-25 | 2014-03-12 | 苏州东菱振动试验仪器有限公司 | Blade high on-line air flow excitation system and test method |
| CN204720053U (en) * | 2015-05-18 | 2015-10-21 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of infrared measurement of temperature simulation device |
| CN205262756U (en) * | 2015-12-25 | 2016-05-25 | 中北大学 | High nip drum stream of engine test device that admits air |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307599A (en) * | 2018-10-15 | 2019-02-05 | 北京矿冶科技集团有限公司 | Test hot environment simulation system, abradable testing machine and temprature control method |
| CN109307599B (en) * | 2018-10-15 | 2020-03-20 | 北京矿冶科技集团有限公司 | High-temperature environment simulation system for test, abradable tester and temperature control method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170215 |