CN105403409A - Moderate thrust aero-engine testing switching device - Google Patents
Moderate thrust aero-engine testing switching device Download PDFInfo
- Publication number
- CN105403409A CN105403409A CN201510915786.4A CN201510915786A CN105403409A CN 105403409 A CN105403409 A CN 105403409A CN 201510915786 A CN201510915786 A CN 201510915786A CN 105403409 A CN105403409 A CN 105403409A
- Authority
- CN
- China
- Prior art keywords
- base
- upper cover
- switching device
- ring
- cover plate
- 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
Links
Classifications
-
- 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 invention provides a moderate thrust aero-engine testing switching device comprising a pedestal, air inlet openings, an inner sealing ring, an upper cover disc, and a pressing plate. The pedestal in the shape of a ring, and is provided with an annular-shaped concave groove. The inner sealing ring is disposed on the inner side top part of the annular-shaped concave groove of the pedestal, and the upper cover disc is disposed on the outer side top part of the annular-shaped concave groove of the pedestal. The outer side surface of the pedestal is provided with more than twenty air inlet openings facing the outer side horizontally, and the air inlet openings are disposed uniformly along the circumference of the pedestal. The position of the pressing plate in the annular-shaped concave groove is fixedly disposed on the bottom surface of the upper cover disc by the bolt. The moderate thrust aero-engine testing switching device is advantageous in that the test of the air flow between the high pressure turbine disc and low pressure turbine disc is simple and convenient, the assembly and the disassembly are easy, and the connection with the device of the test board is convenient; the flow measurement is accurate, and the flowing of the air flow is good.
Description
Technical field
The present invention relates to a kind of medium thrust Aero Engine Testing switching device.
Background technology
In medium thrust Aero Engine Testing, need to carry out airshed test between high and low pressure turbine dish, need control cool air flow path during test, reduce the working temperature of turbo blade, meet working-blade cooling requirement, also to ensure simultaneously and keep appropriate clearance between rotor, meet air system to obturage, in prior art, do not have this suitable device can directly complete this test, need to utilize other device multi-step to carry out, bother very much, and be easy to make mistakes.
Summary of the invention
For solving the problems of the technologies described above, the invention provides a kind of medium thrust Aero Engine Testing switching device, this medium thrust Aero Engine Testing switching device by rational structure ensure that to carry out between high and low pressure turbine dish airshed test succinctly light, be easy to handling.
The present invention is achieved by the following technical programs.
One provided by the invention medium thrust Aero Engine Testing switching device, comprises base, air intake opening, inner seal ring, upper cover plate, pressing plate; Described base is ring-type, by annular concave groove on base; Described inner seal ring is arranged on the inner edge top of base annular concave groove, and described upper cover plate is arranged on the top, outside of base annular concave groove; The outer flank side surface of described base has been horizontally disposed with air intake opening outwardly, and air intake opening quantity is more than 20 and along base circumference uniform distribution; Described pressing plate is bolted on upper cover plate bottom surface at the annular Baltimore groove interior location of base.
By one end end face in the center of circle being provided with the stifled circle of ring-type on described upper cover plate.
Surface of contact between described upper cover plate and base is provided with external seal packing ring.
Described base and inner seal ring are fixed by the screw in vertical direction, and the surface of contact of base and inner seal ring is V-type groove in annulus outer end position, and has interior O-ring seal to be arranged in V-type groove.
The annulus outer end end face of described upper cover plate is fixed with lever.
Beneficial effect of the present invention is: ensure that to carry out between high and low pressure turbine dish airshed test succinctly light, be easy to handling, be convenient to the equipment connection with testing table; Flow measurement is accurate, and air current flow is good.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention when using;
Fig. 2 is structural representation of the present invention.
In figure: 1-base, 2-air intake opening, O-ring seal in 3-, 4-inner seal ring, 5-external seal packing ring, 6-upper cover plate, 7-pressing plate, packing washer in 8-, the stifled circle of 9-, the 10-turbine disk, 11-lever.
Embodiment
Further describe technical scheme of the present invention below, but described in claimed scope is not limited to.
The medium thrust Aero Engine Testing of one as shown in Figure 1 and Figure 2 switching device, comprises base 1, air intake opening 2, inner seal ring 4, upper cover plate 6, pressing plate 7; Described base 1 is ring-type, by annular concave groove on base 1; Described inner seal ring 4 is arranged on the inner edge top of base 1 annular concave groove, and described upper cover plate 6 is arranged on the top, outside of base 1 annular concave groove; The outer flank side surface of described base 1 has been horizontally disposed with air intake opening 2 outwardly, and air intake opening 2 quantity is more than 20 and along base 1 circumference uniform distribution; Described pressing plate 7 is bolted on upper cover plate 6 bottom surface at the annular Baltimore groove interior location of base 1.
For improving sealing effectiveness further, by one end end face in the center of circle being provided with the stifled circle 9 of ring-type on described upper cover plate 6; Surface of contact between described upper cover plate 6 and base 1 is provided with external seal packing ring 5.
For further guaranteeing fixing and sealing effectiveness, described base 1 and inner seal ring 4 are fixed by the screw in vertical direction, and the surface of contact of base 1 and inner seal ring 4 is V-type groove in annulus outer end position, and has interior O-ring seal 3 to be arranged in V-type groove.
For further convenient operation, the annulus outer end end face of described upper cover plate 6 is fixed with lever 11.
Thus, to the turbine disk 10 doing airshed test be needed to be placed in base 1 during use, with upper cover plate 6 and pressing plate 7, the turbine disk 10 is fixedly clamped, the turbine disk 10 inner ring inner seal ring 4 and interior O-ring seal 3 are fixed and guarantee impermeability, can carry out airshed test smoothly subsequently, the set-up mode of air intake opening 2 can guarantee that circumferential gas pressure flow is uniform.
Claims (5)
1. a medium thrust Aero Engine Testing switching device, comprise base (1), air intake opening (2), inner seal ring (4), upper cover plate (6), pressing plate (7), it is characterized in that: described base (1) is ring-type, by annular concave groove on base (1); Described inner seal ring (4) is arranged on the inner edge top of base (1) annular concave groove, and described upper cover plate (6) is arranged on the top, outside of base (1) annular concave groove; The outer flank side surface of described base (1) has been horizontally disposed with air intake opening (2) outwardly, and air intake opening (2) quantity is more than 20 and along base (1) circumference uniform distribution; Described pressing plate (7) is bolted on upper cover plate (6) bottom surface at the annular Baltimore groove interior location of base (1).
2. medium thrust Aero Engine Testing switching device as claimed in claim 1, is characterized in that: the upper stifled circle (9) by one end end face in the center of circle being provided with ring-type of described upper cover plate (6).
3. medium thrust Aero Engine Testing switching device as claimed in claim 1, is characterized in that: the surface of contact between described upper cover plate (6) and base (1) is provided with external seal packing ring (5).
4. medium thrust Aero Engine Testing switching device as claimed in claim 1, it is characterized in that: described base (1) and inner seal ring (4) are fixed by the screw in vertical direction, and the surface of contact of base (1) and inner seal ring (4) is V-type groove in annulus outer end position, and has interior O-ring seal (3) to be arranged in V-type groove.
5. medium thrust Aero Engine Testing switching device as claimed in claim 1, is characterized in that: the annulus outer end end face of described upper cover plate (6) is fixed with lever (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510915786.4A CN105403409A (en) | 2015-12-10 | 2015-12-10 | Moderate thrust aero-engine testing switching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510915786.4A CN105403409A (en) | 2015-12-10 | 2015-12-10 | Moderate thrust aero-engine testing switching device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105403409A true CN105403409A (en) | 2016-03-16 |
Family
ID=55469034
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510915786.4A Pending CN105403409A (en) | 2015-12-10 | 2015-12-10 | Moderate thrust aero-engine testing switching device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105403409A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017935A (en) * | 2016-05-17 | 2016-10-12 | 大连理工大学 | Aero-engine low-pressure turbine shaft split test piece for fastening test, and design method for aero-engine low-pressure turbine shaft split test piece |
| CN109580233A (en) * | 2018-11-20 | 2019-04-05 | 中国航发贵州黎阳航空动力有限公司 | A kind of sealing device for channel gas flow test |
| CN113218661A (en) * | 2021-04-07 | 2021-08-06 | 上海新力动力设备研究所 | Cold air thrust testing device for attitude and orbit control engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201262594Y (en) * | 2008-09-10 | 2009-06-24 | 西安航空发动机（集团）有限公司 | Test device for aerial engine crankcase air mass flow |
| CN102435232A (en) * | 2011-09-05 | 2012-05-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Flow test equipment for inner cavity of engine blade |
| US20140144221A1 (en) * | 2011-05-06 | 2014-05-29 | General Electric Company | Apparatus, system, and method for testing a turbocharger |
| CN203752004U (en) * | 2014-03-03 | 2014-08-06 | 中国燃气涡轮研究院 | Flow testing fixture for guide vanes of turbine |
| CN204177555U (en) * | 2014-05-27 | 2015-02-25 | 北京富华惠航飞机附件维修有限责任公司 | Air traffic flow valve test switching device |
| CN104390786A (en) * | 2014-12-04 | 2015-03-04 | 南京航空航天大学 | Test stand for measuring flow coefficient of small hole under rotation condition |
-
2015
- 2015-12-10 CN CN201510915786.4A patent/CN105403409A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201262594Y (en) * | 2008-09-10 | 2009-06-24 | 西安航空发动机（集团）有限公司 | Test device for aerial engine crankcase air mass flow |
| US20140144221A1 (en) * | 2011-05-06 | 2014-05-29 | General Electric Company | Apparatus, system, and method for testing a turbocharger |
| CN102435232A (en) * | 2011-09-05 | 2012-05-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Flow test equipment for inner cavity of engine blade |
| CN203752004U (en) * | 2014-03-03 | 2014-08-06 | 中国燃气涡轮研究院 | Flow testing fixture for guide vanes of turbine |
| CN204177555U (en) * | 2014-05-27 | 2015-02-25 | 北京富华惠航飞机附件维修有限责任公司 | Air traffic flow valve test switching device |
| CN104390786A (en) * | 2014-12-04 | 2015-03-04 | 南京航空航天大学 | Test stand for measuring flow coefficient of small hole under rotation condition |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017935A (en) * | 2016-05-17 | 2016-10-12 | 大连理工大学 | Aero-engine low-pressure turbine shaft split test piece for fastening test, and design method for aero-engine low-pressure turbine shaft split test piece |
| CN109580233A (en) * | 2018-11-20 | 2019-04-05 | 中国航发贵州黎阳航空动力有限公司 | A kind of sealing device for channel gas flow test |
| CN109580233B (en) * | 2018-11-20 | 2021-05-18 | 中国航发贵州黎阳航空动力有限公司 | Sealing device for channel gas flow test |
| CN113218661A (en) * | 2021-04-07 | 2021-08-06 | 上海新力动力设备研究所 | Cold air thrust testing device for attitude and orbit control engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105403409A (en) | Moderate thrust aero-engine testing switching device | |
| CN203752004U (en) | Flow testing fixture for guide vanes of turbine | |
| CN205209771U (en) | Aeroengine turbine disc gas flow test device | |
| RU2012130351A (en) | TURBINE STEP IN A TURBO MACHINE | |
| CN110018061B (en) | Ultra-high temperature long-time mechanical property testing system with heat-insulating air-cooling clamp | |
| CN202370590U (en) | Turbine blade structure | |
| CN103091046A (en) | Motor graphite end face seal device seal test jig | |
| CN109708824A (en) | Air-tightness detection device, lamp body waterproof construction and air-leakage test and encapsulating method | |
| CN113969982A (en) | Cooling method and structure of cantilever type supercritical carbon dioxide turbine | |
| CN109307577B (en) | Air cooling device for high-temperature vibration test | |
| CN204373848U (en) | A kind of engine cylinder-body water oil channel sealing detects fixture | |
| CN211412049U (en) | Multifunctional experiment cabin of airborne overweight centrifugal simulation device | |
| CN109186908B (en) | Cooling clamping device for high-temperature vibration test of turbine guide vane | |
| CN205209773U (en) | Experimental switching device of removable guide rails | |
| CN202494769U (en) | LED fixing device for LED life test | |
| CN102606366B (en) | Special built-in cantilever type water turbine for cooling tower | |
| CN105334064A (en) | Double-channel flow test switching device | |
| CN110553848B (en) | Multifunctional disc cavity transient response characteristic experiment table | |
| CN211874827U (en) | Prevent centrifugal fan of high temperature usage that leaks | |
| CN203906839U (en) | Pilot-operated type high-temperature diaphragm solenoid valve | |
| CN212275180U (en) | A leakproofness verifying attachment for flange subassembly | |
| CN203636691U (en) | Sealing fixture for pump of gas collecting chamber of compressor casing | |
| CN208269490U (en) | A kind of air channel structure for compressor chamber heat dissipation | |
| CN203772492U (en) | Quick pressure test device for radiant tube | |
| CN108194425B (en) | Cooling structure of grease lubrication molecular pump |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160316 |
|
| RJ01 | Rejection of invention patent application after publication |