CN105547702A - High-temperature and high-voltage testing device for engine case - Google Patents
High-temperature and high-voltage testing device for engine case Download PDFInfo
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- CN105547702A CN105547702A CN201510909048.9A CN201510909048A CN105547702A CN 105547702 A CN105547702 A CN 105547702A CN 201510909048 A CN201510909048 A CN 201510909048A CN 105547702 A CN105547702 A CN 105547702A
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- casing
- ring surface
- high temperature
- test device
- pressurising
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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
Abstract
The invention relates to the technical field of aircraft engine environment simulation, and especially relates to a high-temperature and high-voltage testing device for an engine case. The device comprises a supporting pedestal; an engine case installation frame which is used for fixedly installing the engine case at the top of the supporting pedestal; a pressurizing mechanism which is disposed in the engine case and is controlled to compress the engine case; a pressure sensor which is used for monitoring the pressure of air in a pressurizing capsule; a uniform heat layer, a heating layer and a thermal insulation layer, which are all disposed an inner ring surface of the engine case and the pressurizing capsule, wherein the heating layer is controlled to heat the engine case; and a temperature sensor which is used for monitoring the temperature of the engine case. Through the heating of the engine case and the synchronous applying of a force load, the device is closer to an actual working state of the engine case, can effectively check the thermal and mechanical properties of the engine case at the working state, is high in load simulation precision, and is high in engineering application value.
Description
Technical field
The present invention relates to aviation aircraft engine environmental analogue technique field, particularly relate to a kind of engine crankcase high temperature and pressure test device.
Background technology
Aero-engine casing is as the vitals in engine structure, and it has following vital role on the engine:
1) be connected before and after different casing section, internal face forms complete by-pass air duct air-flow wall jointly, and during work, internal face is subject to high-temperature high-speed airflow and washes away, and need keep profile, guarantee that engine gas flow field meets design requirement under high-temperature and high-pressure conditions;
2) as the main installation frame of engine structure, surface is reserved with in a large number for installing casing annex, the opening installing joint and bleed air line and mounting hole, for as a whole by connecting between engine each several part, maintains structural intergrity.
Therefore in engine working process, be ensure the normal work of engine, casing must have enough rigidity, intensity under the temperature environment of work, prevents deformation instability under its hot conditions.If distortion flexing appears in casing, inlet flow field flow characteristics and the one-piece construction load-carrying properties of engine will be destroyed, cause engine causes vibration, and whole aircraft generation shake and buckling structure can be made time serious to destroy, cause air crash.The complicacy of these loading conditions and structural bearing, makes the design of the structural strength of casing become very crucial problem with evaluation, must to the heat under its condition of work, mechanical property research experiment.
Assessment at present for casing mainly contains following three kinds:
1) adopt temperature correction coefficient, amplify force value and revise, the pressurising capsule adopting rubber to make under normal temperature environment carries out high pressure examination.The method is applicable to the less casing of material property temperature influence, and for the material of easy temperature influence, its correction factor is difficult to determine, and test findings and time of day deviation larger.
2) deep fat pressurising is adopted.This mode is only applicable to material oil-resisting and heat-resisting, the casing that self seal is good, and easily in a high voltage state because casing distortion causes the deep fat of High Temperature High Pressure to leak, poor stability.
3) hot-air pressurising is adopted.This mode can simulate the using state of casing the most truly, but gas thermal capacitance is low, and density is low, is heated to by casing require that temperature and pressure needs a large amount of high temperature air, thus needs custom-made air compressing, and heating, recycle unit, cost is huge.
Along with the development of aeromotor, for meeting high turbine inlet temperature, big thrust loading, large bypass ratio, large overall pressure ratio, and low fuel consumption, the requirement such as life cycle cost and environmental pollution, the structure of engine will adopt a large amount of new material and more large scale obtain casing parts.Therefore need a kind of new test unit to simulate the High Temperature High Pressure duty of casing, to verify the design of engine crankcase.
Summary of the invention
The object of this invention is to provide a kind of engine crankcase high temperature and pressure test device, to solve at least one technical matters above-mentioned.
Technical scheme of the present invention is:
A kind of engine crankcase high temperature and pressure test device, for simulating the high-temperature high-pressure work environment of casing, to verify the structural strength of described casing, described engine crankcase high temperature and pressure test device comprises:
Horizontally disposed support base;
Casing erecting frame, is fixedly connected with the outer ring surface of described casing, and for described casing is fixedly mounted on described support base top, the axes normal of described casing is in surface level;
Pressurising mechanism, be arranged on described casing inner, described pressurising mechanism has the pressurising capsule of tubular, the outer ring surface of the described pressurising capsule after being filled with scheduled volume gas and described casing inner ring surface mating shapes, and described pressurising capsule is used for controllably extruding described casing inner ring surface;
Pressure transducer, is arranged on the inflation inlet place of described pressurising capsule, for monitoring the air pressure in described pressurising capsule;
All tubular even thermosphere, zone of heating and heat-insulation layer, be successively set between described casing inner ring surface and described pressurising capsule outer ring surface from inside to outside, and described zone of heating is used for controllably heating described casing inner ring surface through described even thermosphere;
Temperature sensor, is arranged between described even thermosphere and described casing inner ring surface, for monitoring the surface temperature of described casing.
Preferably, described casing erecting frame comprises:
Trumpet-shaped lower transition section, the bottom of described lower transition section is fixedly connected with described support base upper surface, and the opening diameter bottom described lower transition section is less than the opening diameter at top;
The upper transition section of tubular, the opening diameter of bottom equals the opening diameter at described lower transition section top, and described upper transition section is fixedly connected with by the section top of bottom with described lower transition, jointly to be formed the inner ring surface with described casing outer ring surface mating shapes.
Preferably, described pressurising mechanism also comprises steel cylinder, and described steel cylinder is positioned at described casing inside and is fixed on described support base upper surface, and described pressurising capsule set is arranged on the outer ring surface of described steel cylinder;
Also limiting plate is provided with, for limiting the displacement of described pressurising capsule at vertical direction at the top of described steel cylinder.
Preferably, described even thermosphere is sheet metal, and thickness is not more than 0.5mm, is fixed on described casing inner ring surface by high temperature gummed tape.
Preferably, described zone of heating is the heating tape with resistance wire, and heating power is not less than 1W/cm2.
Preferably, described heat-insulation layer by the first flexible insulant material layer, layer of metal foil, the second flexible insulant material layer and silicane rubber plate flexible insulant material layer from inside to outside successively lay stitching form.
Preferably, described first flexible insulant material layer and described second flexible insulant material layer all adopt fibrage heat-barrier material.
Preferably, described sheet metal is that thickness is not more than 0.5mm.
Preferably, described silicane rubber plate is silicon rubber or the fluororubber that heatproof is not less than 250 DEG C.
The invention has the advantages that:
Engine crankcase high temperature and pressure test device of the present invention is by carrying out the synchronous applying of heat, power load to casing, provide a kind of more close to the test unit of casing actual working state, heat, mechanical property under can effectively examining checking casing in working order, load simulated precision is high, has important engineer applied and is worth.
Accompanying drawing explanation
Fig. 1 is the structure cut-open view of engine crankcase high temperature and pressure test device of the present invention;
Fig. 2 is the enlarged diagram of part A in Fig. 1 of the present invention;
Fig. 3 is the structure cut-open view of pressurising mechanism in engine crankcase high temperature and pressure test device of the present invention.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limiting the scope of the invention can not be interpreted as.
Below in conjunction with accompanying drawing 1 to Fig. 3, engine crankcase high temperature and pressure test device of the present invention is described in further details.
The invention provides a kind of engine crankcase high temperature and pressure test device, for simulating the high-temperature high-pressure work environment of casing 1, to verify the structural strength of casing 1.Engine crankcase high temperature and pressure test device comprises supports base 2, casing erecting frame 3, pressurising mechanism 4 and zone of heating 62 etc.
Support, on the usual horizontally disposed supporting surface (such as ground) of base 2, multiple applicable shape to be set to as required.
Casing erecting frame 3 is mainly used in casing 1 to be fixedly mounted on supports base 2 top.Casing erecting frame 3 has the inner ring surface matched with the outer ring surface of casing 1, to be matched thus is fixedly connected with by casing 1, be in the axes normal of the casing 1 of installment state in surface level by this inner ring surface with the outer ring surface of casing 1; In addition, the bottom of casing erecting frame 3 is fixedly connected with support base 2 top by the mode such as bolt or welding, thus realizes casing 1 to fix.
Casing erecting frame 3 of the present invention can be set to multiple applicable shape according to the shape of casing 1; In the present embodiment, casing erecting frame 3 can comprise lower transition section 31 and upper transition section 32.Lower transition section 31 is in horn-like, and the bottom of lower transition section 31 is fixedly connected with support base 2 upper surface, and the opening diameter bottom lower transition section 31 is less than the opening diameter at top; Upper transition section 32 is in tubular, the opening diameter of bottom equals the opening diameter at lower transition section 31 top, upper transition section 32 is fixedly connected with, jointly to be formed the inner ring surface with casing 1 outer ring surface mating shapes by bolt or the mode such as to weld by the top of bottom and lower transition section 31.It should be noted that, the shape of most of casing 1 is not the cylindrical shape of rule, but be similar to figure look in bottom be horn-like, be therefore conveniently fixed installation, casing erecting frame 3 be divided into upper transition section 32 and lower transition section 31; During installation, first casing 1 is arranged on by lower transition section 31 and supports that on base 2, the upper end of lower transition section 31 reconnects transition section 32.
It is inner that pressurising mechanism 4 is arranged on casing 1, is mainly used in casing 1 and applies pressure load; Pressurising mechanism 4 has the pressurising capsule 41 of tubular, and the outer ring surface of the pressurising capsule 41 after being filled with scheduled volume gas and casing 1 inner ring surface mating shapes, pressurising capsule 41 is for controllably extruding casing 1 inner ring surface.Wherein, because pressurising capsule 41 is deformable bodys, how many meetings of insufflation gas amount impact shape; The scheduled volume gas described in the present embodiment, refers to after being filled with this scheduled volume gas, just makes outer ring surface and the casing 1 inner ring surface mating shapes of pressurising capsule 41, pressurising capsule 41 and casing 1 can be made to fit more complete, apply pressure evenly; When continuing insufflation gas again, can extrude casing 1 inner ring surface.
Further, inflation inlet 42 place of pressurising capsule 41 is provided with pressurising pump (not shown) and pressure transducer 5, for monitoring the air pressure in pressurising capsule 41, thus can control according to the aeration quantity of force value automatic or manual to pressurising capsule 41, automatically control pressurising pump output pressure preferably by computer for controlling according to pressure transducer 5 in the present embodiment, thus control pressurising capsule pressure.
Equally, pressurising mechanism 4 can need to be set to multiple applicable shape according to casing 1; In the present embodiment, pressurising mechanism 4 also comprises steel cylinder 43, and steel cylinder 43 is positioned at casing 1 inside and is fixed on supports base 2 upper surface, and pressurising capsule 41 is set on the outer ring surface of steel cylinder 43; In addition, being also provided with limiting plate 44 at the top of steel cylinder 43, for limiting the displacement of pressurising capsule 41 at vertical direction, making the main extruding that deforms towards casing 1 direction of pressurising capsule 41 in gas replenishment process.
Further, engine crankcase high temperature and pressure test device of the present invention also comprises all tubular even thermosphere 61, zone of heating 62 and heat-insulation layer 63, is successively set between casing 1 inner ring surface and pressurising capsule 41 outer ring surface from inside to outside; Wherein, zone of heating 62 is for controllably heating through even thermosphere 61 pairs of casing 1 inner ring surfaces; In addition, between even thermosphere 61 and casing 1 inner ring surface, be provided with temperature sensor 7, for monitoring the surface temperature of casing 1.
Equally, in the present invention, the temperature value automatic or manual can monitored according to temperature sensor 7 controls zone of heating 62; In the present embodiment, zone of heating 62 by Power supply, the temperature value automatic control power supply output power that computer for controlling is monitored according to temperature sensor 7, thus control zone of heating 62 heating-up temperature.
In engine crankcase high temperature and pressure test device of the present invention, the concrete structure of even thermosphere 61, zone of heating 62 and heat-insulation layer 63 can carry out the selection be applicable to as required.In the present embodiment, even thermosphere 61 is sheet metal, and thickness is not more than 0.5mm, can soft conformable casing 1 surface, be fixed on casing 1 inner ring surface by high temperature gummed tape.Zone of heating 62 is glass wool cloth Resistant heating band, can soft conformable casing 1 surface, heating power is not less than 1W/cm2, and is fixed by high temperature gummed tape.
Heat-insulation layer 63 by can the first flexible insulant material layer, layer of metal foil, the second flexible insulant material layer and silicane rubber plate flexible insulant material layer from inside to outside successively lay stitching form.Wherein, the first flexible insulant material layer and the second flexible insulant material layer all adopt fibrage heat-barrier material, for reducing heat conduction; Sheet metal is the high heat conductivity metal material that thickness is not more than 0.5mm, for soaking, avoids local temperature too high; Silicane rubber plate is silicon rubber or the fluororubber that heatproof is not less than 250 DEG C, utilizes the feature that its thermal capacitance is large, absorbs heat, reduces temperature rise amplitude.
Engine crankcase high temperature and pressure test device of the present invention is by carrying out the synchronous applying of heat, power load to casing, provide a kind of more close to the test unit of casing actual working state, heat, mechanical property under can effectively examining checking casing in working order, load simulated precision is high, has important engineer applied and is worth; In addition, material therefor number of devices of the present invention is few, and cost is low, and reliability is high; Further, the present invention does not relate to high-temperature gas or liquid, and security is good.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (9)
1. an engine crankcase high temperature and pressure test device, for simulating the high-temperature high-pressure work environment of casing (1), to verify the structural strength of described casing (1), it is characterized in that, described engine crankcase high temperature and pressure test device comprises:
Horizontally disposed support base (2);
Casing erecting frame (3), be fixedly connected with the outer ring surface of described casing (1), and for described casing (1) being fixedly mounted on described support base (2) top, the axes normal of described casing (1) is in surface level;
Pressurising mechanism (4), be arranged on described casing (1) inner, described pressurising mechanism (4) has the pressurising capsule (41) of tubular, the outer ring surface of the described pressurising capsule (41) after being filled with scheduled volume gas and described casing (1) inner ring surface mating shapes, described pressurising capsule (41) is for controllably extruding described casing (1) inner ring surface;
Pressure transducer (5), is arranged on inflation inlet (42) place of described pressurising capsule (41), for monitoring the air pressure in described pressurising capsule (41);
All tubular even thermosphere (61), zone of heating (62) and heat-insulation layer (63), be successively set between described casing (1) inner ring surface and described pressurising capsule (41) outer ring surface from inside to outside, described zone of heating (62) is for controllably heating described casing (1) inner ring surface through described even thermosphere (61);
Temperature sensor (7), is arranged between described even thermosphere (61) and described casing (1) inner ring surface, for monitoring the surface temperature of described casing (1).
2. engine crankcase high temperature and pressure test device according to claim 1, is characterized in that, described casing erecting frame (3) comprising:
Trumpet-shaped lower transition section (31), the bottom of described lower transition section (31) is fixedly connected with described support base (2) upper surface, and the opening diameter of described lower transition section (31) bottom is less than the opening diameter at top;
The upper transition section (32) of tubular, the opening diameter of bottom equals the opening diameter at described lower transition section (31) top, described upper transition section (32) is fixedly connected with by the top of bottom with described lower transition section (31), jointly to be formed the inner ring surface with described casing (1) outer ring surface mating shapes.
3. engine crankcase high temperature and pressure test device according to claim 1, it is characterized in that, described pressurising mechanism (4) also comprises steel cylinder (43), described steel cylinder (43) is positioned at described casing (1) inside and is fixed on described support base (2) upper surface, and described pressurising capsule (41) is set on the outer ring surface of described steel cylinder (43);
Limiting plate (44) is also provided with, for limiting the displacement of described pressurising capsule (41) at vertical direction at the top of described steel cylinder (43).
4. engine crankcase high temperature and pressure test device according to claim 1, is characterized in that, described even thermosphere (61) is sheet metal, and thickness is not more than 0.5mm, is fixed on described casing (1) inner ring surface by high temperature gummed tape.
5. engine crankcase high temperature and pressure test device according to claim 4, is characterized in that, described zone of heating (62) is for having the heating tape of resistance wire, and heating power is not less than 1W/cm2.
6. engine crankcase high temperature and pressure test device according to claim 5, it is characterized in that, described heat-insulation layer (63) is laid stitching from inside to outside successively by the first flexible insulant material layer, layer of metal foil, the second flexible insulant material layer and silicane rubber plate flexible insulant material layer and is formed.
7. engine crankcase high temperature and pressure test device according to claim 6, is characterized in that, described first flexible insulant material layer and described second flexible insulant material layer all adopt fibrage heat-barrier material.
8. engine crankcase high temperature and pressure test device according to claim 6, is characterized in that, described sheet metal is that thickness is not more than 0.5mm.
9. engine crankcase high temperature and pressure test device according to claim 6, is characterized in that, described silicane rubber plate is silicon rubber or the fluororubber that heatproof is not less than 250 DEG C.
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| CN201510909048.9A CN105547702B (en) | 2015-12-10 | 2015-12-10 | A kind of engine crankcase high temperature and pressure test device |
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| CN201510909048.9A CN105547702B (en) | 2015-12-10 | 2015-12-10 | A kind of engine crankcase high temperature and pressure test device |
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| CN105547702A true CN105547702A (en) | 2016-05-04 |
| CN105547702B CN105547702B (en) | 2018-04-13 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107063695A (en) * | 2017-04-26 | 2017-08-18 | 中国燃气涡轮研究院 | A kind of aeroengine combustor buring room water-cooled casing reinforcement structure |
| CN108918147A (en) * | 2018-06-21 | 2018-11-30 | 南京航空航天大学 | It is a kind of bilayer targeting testing device and hot environment test method |
| CN110361195A (en) * | 2019-07-19 | 2019-10-22 | 中国航发沈阳发动机研究所 | A kind of accessory drive gearbox test heat chamber simulator |
| CN110926781A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Cartridge receiver hot-pressing combined loading test device and using method thereof |
| CN112985787A (en) * | 2021-02-01 | 2021-06-18 | 中国航发沈阳发动机研究所 | Card installing mechanism for high-temperature test of case |
| CN113776950A (en) * | 2021-08-16 | 2021-12-10 | 中国航发贵阳发动机设计研究所 | Water bag structure for pressure test of special-shaped casing and mounting method thereof |
| CN113899554A (en) * | 2021-12-10 | 2022-01-07 | 中国飞机强度研究所 | Balance control method for slow-vehicle running environment field of laboratory aircraft engine |
| CN113959860A (en) * | 2021-12-20 | 2022-01-21 | 天津航天瑞莱科技有限公司 | Thermal internal pressure test system for casing piece in pneumatic-hydraulic loading mode |
| CN113984361A (en) * | 2021-10-26 | 2022-01-28 | 中国航发沈阳发动机研究所 | Engine case internal pressure test device |
| CN117554083A (en) * | 2024-01-11 | 2024-02-13 | 天津航天瑞莱科技有限公司 | Method for loading system by adopting engine casing thermal internal pressure fatigue test |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107063695A (en) * | 2017-04-26 | 2017-08-18 | 中国燃气涡轮研究院 | A kind of aeroengine combustor buring room water-cooled casing reinforcement structure |
| CN108918147A (en) * | 2018-06-21 | 2018-11-30 | 南京航空航天大学 | It is a kind of bilayer targeting testing device and hot environment test method |
| CN110361195B (en) * | 2019-07-19 | 2021-03-12 | 中国航发沈阳发动机研究所 | Experimental high-temperature chamber analogue means of annex machine casket |
| CN110361195A (en) * | 2019-07-19 | 2019-10-22 | 中国航发沈阳发动机研究所 | A kind of accessory drive gearbox test heat chamber simulator |
| CN110926781B (en) * | 2019-12-05 | 2021-07-20 | 中国航发四川燃气涡轮研究院 | Cartridge receiver hot-pressing combined loading test device and using method thereof |
| CN110926781A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Cartridge receiver hot-pressing combined loading test device and using method thereof |
| CN112985787A (en) * | 2021-02-01 | 2021-06-18 | 中国航发沈阳发动机研究所 | Card installing mechanism for high-temperature test of case |
| CN113776950A (en) * | 2021-08-16 | 2021-12-10 | 中国航发贵阳发动机设计研究所 | Water bag structure for pressure test of special-shaped casing and mounting method thereof |
| CN113984361A (en) * | 2021-10-26 | 2022-01-28 | 中国航发沈阳发动机研究所 | Engine case internal pressure test device |
| CN113899554A (en) * | 2021-12-10 | 2022-01-07 | 中国飞机强度研究所 | Balance control method for slow-vehicle running environment field of laboratory aircraft engine |
| CN113899554B (en) * | 2021-12-10 | 2022-02-18 | 中国飞机强度研究所 | Balance control method for slow-vehicle running environment field of laboratory aircraft engine |
| CN113959860A (en) * | 2021-12-20 | 2022-01-21 | 天津航天瑞莱科技有限公司 | Thermal internal pressure test system for casing piece in pneumatic-hydraulic loading mode |
| CN117554083A (en) * | 2024-01-11 | 2024-02-13 | 天津航天瑞莱科技有限公司 | Method for loading system by adopting engine casing thermal internal pressure fatigue test |
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| CN105547702B (en) | 2018-04-13 |
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