CN109798771A - One kind testing heating device for aero-engine turbine disk low cycle fatigue life - Google Patents
One kind testing heating device for aero-engine turbine disk low cycle fatigue life Download PDFInfo
- Publication number
- CN109798771A CN109798771A CN201910098471.3A CN201910098471A CN109798771A CN 109798771 A CN109798771 A CN 109798771A CN 201910098471 A CN201910098471 A CN 201910098471A CN 109798771 A CN109798771 A CN 109798771A
- Authority
- CN
- China
- Prior art keywords
- turbine disk
- furnace
- aero
- fatigue life
- heating device
- 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
- 238000010438 heat treatment Methods 0.000 title claims abstract description 81
- 238000012360 testing method Methods 0.000 title claims abstract description 76
- 230000005855 radiation Effects 0.000 claims abstract description 9
- 239000012774 insulation material Substances 0.000 claims description 15
- 238000009529 body temperature measurement Methods 0.000 claims description 8
- 239000000835 fiber Substances 0.000 claims description 8
- BPQQTUXANYXVAA-UHFFFAOYSA-N Orthosilicate Chemical compound [O-][Si]([O-])([O-])[O-] BPQQTUXANYXVAA-UHFFFAOYSA-N 0.000 claims description 7
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 7
- 238000001816 cooling Methods 0.000 claims description 5
- 238000001514 detection method Methods 0.000 claims description 4
- 239000011810 insulating material Substances 0.000 claims 1
- 239000011229 interlayer Substances 0.000 abstract description 7
- 238000009434 installation Methods 0.000 description 9
- 230000006378 damage Effects 0.000 description 7
- 239000010425 asbestos Substances 0.000 description 6
- 229910052895 riebeckite Inorganic materials 0.000 description 6
- 230000035882 stress Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000007789 sealing Methods 0.000 description 4
- 229910001220 stainless steel Inorganic materials 0.000 description 4
- 239000010935 stainless steel Substances 0.000 description 4
- 239000004744 fabric Substances 0.000 description 3
- 238000009413 insulation Methods 0.000 description 3
- 229910052573 porcelain Inorganic materials 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000005245 sintering Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000010410 dusting Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000004154 testing of material Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000005619 thermoelectricity Effects 0.000 description 1
- 238000007666 vacuum forming Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
It is provided by the invention a kind of for aero-engine turbine disk low cycle fatigue life test heating device, heating element is separately positioned in the interlayer of furnace bottom, bonnet and furnace roof, turbine disk test assembly is heated by the way of heat radiation, heat radiation heating is uniformly heated turbine disk test assembly, and more energy saving.Meanwhile heating element being avoided to occupy the space of furnace body, the internal working volume of furnace body is increased indirectly, so that furnace body is suitable for the hot test of the turbine disk test assembly of any model, is improved the security performance of test.
Description
Technical field
The present invention relates to aero-engine test technologies, specially a kind of to be used for aero-engine turbine disk low-cycle fatigue
Life test heating device.
Background technique
Aero-engine turbine disk is attached to compressor by main shaft and compressor is driven to rotate, and turbine disk destruction can jeopardize
Flight safety causes extremely serious consequence, therefore it is required that the turbine disk has very high reliability.When engine operation, turbine
Disk subjects the loads such as biggish torque, axial force, gyroscopic couple, centrifugal force and vibration, in the whirlpool of engine high-temperature area work
Wheel disc, in addition to by centrifugal force and vibrational loading, thermic load is the turbine disk by one of Main Load, these are to engine turbine
Disk fatigue life is affected.Stress analysis and the testing of materials are only leaned on, can't accurately expect the fatigue life of the turbine disk.Whirlpool
Wheel disc test is the examination position that desired load is applied to the turbine disk by rotation test device, and the true simulation turbine disk is examined
The service load and state of temperature at core position guarantee that the turbine disk has the boundary condition and temperature environment of engine flight state.
By carrying out static strength examination or fatigue life test verifying to the turbine disk under hot state environment, verifies its static strength or provide predetermined
Safe cycle life.
Due to the needs on engine structure, the turbine disk is often designed to different geometries, is machined with platform on it
The geometries such as rank, hole, tongue-and-groove, spline, these positions are all the crucial portions of the position that turbine disk stress is concentrated and the turbine disk
Position, usual local stress is very high, and the service life of the turbine disk is typically all to be determined by the very high dangerouse cross-section of these local stresses.Separately
Outside, influence of the temperature to testpieces fatigue life first is that material mechanical performance is caused to decline causes testpieces tired there are two aspect
The labor service life reduces；Second is that non-uniform Temperature Distribution generates thermal stress in testpieces to be made together with mechanical stress with engine
Changed with circulation, causes the fatigue rupture of testpieces.
In the past when carrying out engine turbine disk hot test on " vertical rotating exerciser ", wanted to reach temperature field
It asks, can only be tested for the turbine disk of a certain model.Original equipment heating system is tower structure, with asbestos cloth package every
Heat is surrounded testpieces and heater with the double-layer stainless steel for being sandwiched between heat-insulated asbestos cloth that is, outside testpieces, to prevent
Only heat distributes.Heater is made of resistance wire and porcelain stick, as shown in Fig. 2, not only installing cumbersome and being easily damaged, Mei Gezhi
Frame fixes the heater of 4 1KW, is separately mounted to top spacer, bottom baffles, surveys on the partition of face, occupies internal a large amount of empty
Between.The heater being particularly wall-mounted at the top of exerciser, when turbine disk high speed rotation, porcelain stick can smash test because vibrating breakage
Part causes testpieces to damage and rupture without reason.While it to be also passed through appropriate air, and air intlet, to prevent because vacuum degree is excessively high,
The resistance wire of heater is caused to damage because of ionization, as shown in Figure 1.
Therefore, it is necessary to be improved to pervious heating means.The device is set to adapt to Multiple Type engine turbine disk
Hot test, and improve the safety of test.
Summary of the invention
Aiming at the problems existing in the prior art, the present invention provides a kind of for aero-engine turbine disk low-cycle fatigue
Life test heating device, can adapt to the hot test requirement of Multiple Type engine turbine disk, and increase heating device
Internal use space provides condition for the installation of other testing equipments.
The present invention is to be achieved through the following technical solutions:
One kind testing heating device, including furnace body, heating element for aero-engine turbine disk low cycle fatigue life
And electroheat pair；
Wherein, furnace body packet bonnet and the furnace roof and furnace bottom that are separately positioned at the top and bottom of it, bonnet, furnace roof and furnace bottom
Structure it is identical, be made of shell and interior lining panel, between shell and interior lining panel be filled with thermal insulation material and heating element, heating
Element is connect with temperature control device, and heating element heats turbine disk test assembly by heat radiation；
Furnace roof is provided centrally with connecting shaft, and the lower end of connecting shaft is located in furnace body, for connecting turbine disk test assembly,
The upper end of connecting shaft passes through the rotation axis connection of furnace roof and exerciser；
Electroheat pair is provided at the top of the bottom of furnace roof and furnace bottom, electroheat pair is connect with detection system, electroheat pair difference
For measuring the temperature at the top and bottom of turbine disk test assembly.
Preferably, cooling air channel is set between the shell and thermal insulation material, for reducing the temperature of shell.
Preferably, the thermal insulation material is alumina silicate fibre.
Preferably, the material of the heating element is the heating tape of Cr20Ni80.
Preferably, it is provided with connecting bracket at the top of the furnace roof, for furnace roof to be connect with exerciser top cover.
Preferably, multiple electroheat pair mounting holes are evenly distributed on the furnace roof and furnace bottom, electroheat pair mounting hole is item
Shape hole, the length direction of strip-shaped hole are the radial direction of furnace roof.
Preferably, it is evenly distributed with three groups of heating elements respectively in the furnace roof and furnace bottom, is evenly distributed in six groups of heating in bonnet
Element.
Preferably, the furnace bottom is provided centrally with air inlet.
Preferably, it is provided with telescope support on the side wall of the bonnet, thermocouple temperature measurement component, furnace are set on telescope support
The side wall of cover is additionally provided with thermometer hole, and telescope support can be such that thermocouple temperature measurement component tries by the turbine disk of the thermometer hole to furnace body
It tests component and carries out thermometric.
Preferably, the furnace roof, bonnet and furnace bottom are connected by positioning and guiding bar.
Compared with prior art, the invention has the following beneficial technical effects:
It is provided by the present application a kind of for aero-engine turbine disk low cycle fatigue life test heating device, it will heat
Element is separately positioned in the interlayer of furnace bottom, bonnet and furnace roof, is added by the way of heat radiation to turbine disk test assembly
Heat, heat radiation heating are uniformly heated turbine disk test assembly, and more energy saving.Meanwhile heating element is embedded in
It in interlayer, avoids heating element from occupying the space of furnace body, increases the internal working volume of furnace body indirectly, furnace body is made to be suitable for appointing
The hot test of the turbine disk test assembly of what model.In addition, during the test, turbine disk test assembly high speed rotation, by
Be embedded in interlayer in heating element, therefore solve turbine disk test assembly high speed rotation in the prior art, cause heating rod because
The problem of vibration can smash testpieces, testpieces is caused to damage and rupture without reason avoids that experiment accident occurs, improves the peace of test
Full performance.
Environment is conducive to using alumina silicate fibre thermal insulation material, while avoiding the harm to operator, service life
It is long, it reduces costs.
Heating element uses Cr20Ni80 material, meets that testpieces is up to the heating of 700 DEG C of test temperatures and thermometric is wanted
It asks, improves the test temperature section of equipment.The manual temperature of original equipment is further adjusted into control, is improved to PID closed loop certainly
Dynamic control makes temperature control error and is increased to 1% from 3%, improves test accuracy.
Detailed description of the invention
Fig. 1 is existing heater structure schematic diagram；
Fig. 2 is former heater heating rod structural schematic diagram；
Fig. 3 is the structural schematic diagram of heating device of the present invention；
Fig. 4 is the top view of heating device of the present invention；
Fig. 5 is the schematic diagram of heating element of the present invention.
In figure: 1, exerciser top cover；2, connecting bracket；3, rotary shaft；4, Coupling Shaft；5, furnace roof；7, telescope support；8, hot
Galvanic couple temperature measurement component；9, bonnet；10, turbine disk test assembly；11, air inlet；12, furnace bottom；13, electroheat pair；13, positioning and guiding
Bar.
Specific embodiment
Present invention will be described in further detail below with reference to the accompanying drawings, described to be explanation of the invention rather than limit
It is fixed.
Shown in Fig. 3 and Fig. 4, one kind testing heating device for aero-engine turbine disk low cycle fatigue life, including
Furnace body, heating component and temperature measurement component.
Wherein, furnace body includes furnace roof 5, bonnet 9 and furnace bottom 12；The bonnet 9 be it is columnar structured, furnace roof 5 be arranged in bonnet 9
Top, the bottom of bonnet 9 is arranged in furnace bottom 12.
Furnace roof 5 is provided centrally with central axis hole, and connecting shaft 4 is provided in central axis hole, and the lower end of connecting shaft 4 is located at furnace body
In, the lower end of connecting shaft 4 passes through the rotation of furnace roof 5 and exerciser for connecting turbine disk test assembly 10, the upper end of connecting shaft
Axis 3 connects, and the top circumference of furnace roof 5 is evenly equipped with multiple connecting brackets 2, and furnace roof 5 is connected by connecting bracket 2 and exerciser top cover 1
It connects.Connecting bracket 2 is the channel steel of c-type structure, and the strip-shaped hole for installing bolt, connection are provided at the top and bottom of channel steel
The load-bearing of bracket 2 is greater than 600Kg.
Furnace roof 5 is disc, including shell and interior lining panel made of stainless steel plate, outer casing thickness 4mm, thickness of inner lining
1.5mm fills thermal insulation material and installation heating element, wind is arranged between thermal insulation material and shell between shell and interior lining panel
Road, for cooling down to shell, the both ends in air duct are provided with connector, for connecting cold duct.
Three galvanic couple mounting holes, each 120 degree of interval are evenly distributed in out on furnace roof 5, galvanic couple mounting hole is strip-shaped hole, item
The axial direction in shape hole is the diametrical direction of furnace roof, and the electroheat pair 13 being installed therein is enable to adjust installation site, electricity along strip-shaped hole
Thermocouple 13 and the sealing of galvanic couple mounting hole are installed, and so that it is had sealing heat insulating function, are prevented the heat loss in furnace body, electroheat pair 13
Lower end pass through galvanic couple mounting hole and be located at turbine disk test assembly top, for measuring 10 bottom of turbine disk test assembly
Temperature.
Bonnet 9 is columnar structured, including shell and interior lining panel made of stainless steel plate, outer casing thickness 4mm, interior liner thickness
1.5mm, 1200 × 800mm of interior chamber size Φ of bonnet 9 are spent, thermal insulation material and installation heating are filled between shell and interior lining panel
Air duct is arranged in element between thermal insulation material and shell, for cooling down to shell, the both ends in air duct are provided with connector, for connecting
Cold duct.Square hole is offered on the side wall of bonnet 9, having a size of 80 × 715mm, connects telescope support on the outer wall of bonnet 9
7, thermocouple temperature measurement component 8 is set on telescope support 7, and telescope support 7 can make thermocouple temperature measurement component 8 pass through square hole entrance
Thermometric is carried out to turbine disk test assembly in furnace body.
Furnace bottom 12 is disc, including shell and interior lining panel made of stainless steel plate, outer casing thickness 4mm, thickness of inner lining
1.5mm fills thermal insulation material and installation heating element, wind is arranged between thermal insulation material and shell between shell and interior lining panel
Road, for cooling down to shell, the both ends in air duct are provided with connector, for connecting cold duct.
Three galvanic couple mounting holes, each 120 degree of interval are evenly distributed in out on furnace bottom 12, galvanic couple mounting hole is strip-shaped hole,
The axial direction of strip-shaped hole is the diametrical direction of furnace roof, and the electroheat pair 13 being installed therein is enable to adjust installation site along strip-shaped hole,
Electroheat pair 13 and the sealing of galvanic couple mounting hole are installed, and so that it is had sealing heat insulating function, are prevented the heat loss in furnace body, electroheat pair
13 lower end passes through galvanic couple mounting hole and is located at the lower section of turbine disk test assembly, for measuring 10 bottom of turbine disk test assembly
Temperature.The center of furnace bottom 12 is additionally provided with air inlet 11, to prevent vacuum degree excessively high.
Since furnace roof 5, furnace bottom 12 and 9 bulk-breaking of bonnet independently make, combined during installation using multiple positioning and guiding bars 14
Connection, multiple 14 circumference uniform distributions of positioning and guiding bar are on 9 side wall of bonnet, convenient for frequently dismounting, and install convenient.Positioning and guiding bar
Including positioning plate and guide rod, locating rod is vertically mounted on the side wall of furnace roof 5 by connecting plate, and the lower end of locating rod is tapered
Structure, positioning plate are horizontally arranged on the shell of bonnet 9, and location hole is provided on positioning plate, and locating rod is inserted into location hole
In be located by connecting to furnace roof 5 and bonnet 9.
Furnace roof 5, furnace bottom 12 and bonnet 9 are all made of identical heating element, heating element Cr20Ni80, operating temperature
600 DEG C, it is firm that heating element requires to be fixedly mounted, and must not fall off under test conditions.Heating element is controlled automatically using PID closed loop
System, buying Xi'an perseverance pacify electric heater control cabinet.
Three groups of heating elements are respectively set in furnace roof 5 and furnace bottom 12, six groups of heating elements point are set in bonnet 9, and every group only
Vertical to draw wiring, six groups of heating elements in bonnet 9 divide circumference uniform distribution, and the connecting terminal of heating element respectively corresponds fixed installation
On furnace roof 5, furnace bottom 12, bonnet 9, connecting terminal require with corresponding casing insulation, and facilitate frequent wiring.
Heating element includes heating tape, fixed column and the connection terminal of Cr20Ni80, and fixed column is fixed on thermal insulation material,
Multiple fixed columns are uniformly distributed, and heating tape is connect with fixed column, and the both ends of heating tape are connect with binding post.Heating unit on bonnet
Part is ring structure, and six groups of heating elements are uniformly distributed from top to bottom.
The detection of thermoelectricity even synchronization, temperature uniformity ± 15 DEG C, detection temperature spot are 700 DEG C.Temperature-measuring range Φ 1200 ×
800mm。
Thermal insulation material use alumina silicate fibre vacuum forming part, 1200 DEG C of high temperature resistant.After alumina silicate fibre forming and sintering part
Firm in structure, heat insulation effect is good, and not dusting is not scaling-off, can satisfy job requirement under vacuum conditions.The requirement of forming and sintering part
Convenient for the fixation and installation of heating element.Heating element and thermocouple fairlead have insulation protection.Furnace shell hull-skin temperature
Less than 80 DEG C.
It is provided by the present application a kind of for aero-engine turbine disk low cycle fatigue life test heating device, it will heat
Element is separately positioned in the interlayer of furnace bottom, bonnet and furnace roof, is added by the way of heat radiation to turbine disk test assembly
Heat directly heat compared with mode using heating rod with existing, and heat radiation heating keeps turbine disk test assembly heated more
Add uniformly, and more energy saving.
Secondly, existing heater is made of resistance wire and porcelain stick, not only installs cumbersome and be easily damaged, each bracket
The heater of 4 1KW is fixed, the internal holes of heater are largely occupied, reduces the scope of application of heater；The application's adds
Thermal element is embedded in interlayer, is avoided heating element from occupying the space of furnace body, is increased the internal working volume of furnace body indirectly, together
Shi Caiyong heat radiation heating, makes furnace body be suitable for the hot test of the turbine disk test assembly of any model.
In addition, during the test, turbine disk test assembly high speed rotation, since heating element is embedded in interlayer, because
This solves turbine disk test assembly high speed rotation in the prior art, causes heating rod because vibration can smash testpieces, causes to test
The problem of part is damaged and ruptured without reason avoids that experiment accident occurs, improves the security performance of test.
Alumina silicate fibre thermal insulation material is respectively set in furnace bottom, bonnet and furnace roof, caused by greatly reducing thermal convection
Turbine disk testpieces upper and lower surfaces temperature difference Pass Test requirement has been protected just in temperature loss.Testing proves, after applying the present invention whirlpool
Within Cha≤15 DEG C wheel disc testpieces upper and lower surfaces Wen.
It is existing to be caused damages to personnel using asbestos cloth；Part asbestos fibre is discharged into test bay by vacuum pump and makes
At environmental pollution；Asbestos often can only be disposable, and asbestos dangerous waste discharge amount can be brought to increase.It compares, using alumina silicate
Fiber heat preservation material is conducive to environment, while avoiding the harm to operator, and long service life reduces costs.
Heating element uses Cr20Ni80 material, meets that testpieces is up to the heating of 700 DEG C of test temperatures and thermometric is wanted
It asks, heats Zong Gong Shuai≤48KW.The manual temperature of original equipment is adjusted into control, error is big and turbine disk test assembly 10 is upper and lower
The temperature gap on surface is larger, it is difficult to which the needs for meeting turbine disk test are improved to PID closed-loop automatic control, make temperature control
Error is increased to 1% from 3%.
The above content is merely illustrative of the invention's technical idea, and this does not limit the scope of protection of the present invention, all to press
According to technical idea proposed by the present invention, any changes made on the basis of the technical scheme each falls within claims of the present invention
Protection scope within.
Claims (10)
1. one kind for aero-engine turbine disk low cycle fatigue life test heating device, which is characterized in that including furnace body,
Heating element and electroheat pair；
Wherein, furnace body packet bonnet (9) and the furnace roof (5) and furnace bottom (12) that are separately positioned at the top and bottom of it, bonnet (9),
Furnace roof (5) is identical with the structure of furnace bottom (12), is made of shell and interior lining panel, and thermal insulating material is filled between shell and interior lining panel
Material and heating element, heating element connect with temperature control device, heating element pass through heat radiation to turbine disk test assembly (10) into
Row heating；
Furnace roof (5) is provided centrally with connecting shaft (4), and the lower end of connecting shaft (4) is located in furnace body, for connecting turbine disk test
Component (10), the upper end of connecting shaft pass through furnace roof (5) and connect with the rotary shaft (3) of exerciser；
It is provided with electroheat pair at the top of the bottom of furnace roof (5) and furnace bottom (12), electroheat pair is connect with detection system, electroheat pair point
The temperature at the top and bottom of turbine disk test assembly (10) Yong Yu not measured.
2. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, cooling air channel is set between the shell and thermal insulation material, for reducing the temperature of shell.
3. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, the thermal insulation material is alumina silicate fibre.
4. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, the material of the heating element is the heating tape of Cr20Ni80.
5. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, is provided with connecting bracket at the top of the furnace roof (5), for furnace roof (5) to be connect with exerciser top cover (1).
6. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, multiple electroheat pair mounting holes are evenly distributed on the furnace roof (5) and furnace bottom (12), and electroheat pair mounting hole is bar shaped
Hole, the length direction of strip-shaped hole are the radial direction of furnace roof (5).
7. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, is evenly distributed with three groups of heating elements in the furnace roof (5) and furnace bottom (12) respectively, is evenly distributed in six groups of heating in bonnet (9)
Element.
8. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, the furnace bottom (12) is provided centrally with air inlet (11).
9. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, is provided with telescope support (7) on the side wall of the bonnet (9), thermocouple temperature measurement component (8) is set on telescope support (7),
The side wall of bonnet (9) is additionally provided with thermometer hole, and telescope support (7) can make thermocouple temperature measurement component (8) by thermometer hole to furnace
The turbine disk test assembly of body carries out thermometric.
10. testing heating device, feature for aero-engine turbine disk low cycle fatigue life according to claim 1
It is, the furnace roof (5), bonnet (9) and furnace bottom (12) are connected by positioning and guiding bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910098471.3A CN109798771A (en) | 2019-01-31 | 2019-01-31 | One kind testing heating device for aero-engine turbine disk low cycle fatigue life |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910098471.3A CN109798771A (en) | 2019-01-31 | 2019-01-31 | One kind testing heating device for aero-engine turbine disk low cycle fatigue life |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109798771A true CN109798771A (en) | 2019-05-24 |
Family
ID=66560855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910098471.3A Pending CN109798771A (en) | 2019-01-31 | 2019-01-31 | One kind testing heating device for aero-engine turbine disk low cycle fatigue life |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109798771A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112014110A (en) * | 2020-07-31 | 2020-12-01 | 中国航发贵阳发动机设计研究所 | Temperature field control device of vertical wheel disc low-cycle fatigue tester |
| WO2020252983A1 (en) * | 2019-06-20 | 2020-12-24 | 浙江大学 | Material performance testing system under fixed multi-field coupling action in supergravity environment |
| CN112179661A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Heating device for wheel disc test |
| CN114136640A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Online adjustable gradient heating device for strength test of aero-engine wheel disc |
| CN114593606A (en) * | 2022-03-17 | 2022-06-07 | 中国航发沈阳发动机研究所 | A split vertical rotor heating device |
| CN116046195A (en) * | 2023-04-03 | 2023-05-02 | 中国航发四川燃气涡轮研究院 | Movable type aeroengine wheel disk temperature measuring device |
| FR3152881A1 (en) * | 2023-09-13 | 2025-03-14 | Safran Aircraft Engines | Self-retracting thermocouple for test bench |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5517852A (en) * | 1994-11-02 | 1996-05-21 | Standard Aero Limited | Diagnostic performance testing for gas turbine engines |
| JPH08313168A (en) * | 1995-05-23 | 1996-11-29 | Ishikawajima Harima Heavy Ind Co Ltd | Space electric furnace structure |
| CN102717518A (en) * | 2012-06-25 | 2012-10-10 | 江苏大学 | Integrated manufacture and testing device and testing method for carbon fiber composite material |
| CN103267636A (en) * | 2013-05-10 | 2013-08-28 | 西安航空动力股份有限公司 | Heating device for aero-engine spindle thermal state strength test |
| CN103697695A (en) * | 2013-12-03 | 2014-04-02 | 朱子勤 | Atmosphere box type protection experiment stove |
| CN204944818U (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of inside rotating disc cavities fluid interchange test unit |
| CN205174394U (en) * | 2015-12-07 | 2016-04-20 | 天津商业大学 | Small -size burning furnace temperature measuring device that burns |
| CN205426522U (en) * | 2016-02-01 | 2016-08-03 | 浙江大学 | Heating of aeroengine blade flies disconnected device based on local heating principle |
| CN106289734A (en) * | 2016-07-21 | 2017-01-04 | 浙江大学 | A kind of aero-engine casing high temperature containment test technology |
| CN106839771A (en) * | 2017-02-23 | 2017-06-13 | 中国航发沈阳发动机研究所 | A kind of vertical rotor heating apparatus and system |
| CN207123169U (en) * | 2017-09-13 | 2018-03-20 | 河钢股份有限公司 | A kind of special heating furnace for fatigue at high temperature test |
-
2019
- 2019-01-31 CN CN201910098471.3A patent/CN109798771A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5517852A (en) * | 1994-11-02 | 1996-05-21 | Standard Aero Limited | Diagnostic performance testing for gas turbine engines |
| JPH08313168A (en) * | 1995-05-23 | 1996-11-29 | Ishikawajima Harima Heavy Ind Co Ltd | Space electric furnace structure |
| CN102717518A (en) * | 2012-06-25 | 2012-10-10 | 江苏大学 | Integrated manufacture and testing device and testing method for carbon fiber composite material |
| CN103267636A (en) * | 2013-05-10 | 2013-08-28 | 西安航空动力股份有限公司 | Heating device for aero-engine spindle thermal state strength test |
| CN103697695A (en) * | 2013-12-03 | 2014-04-02 | 朱子勤 | Atmosphere box type protection experiment stove |
| CN204944818U (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of inside rotating disc cavities fluid interchange test unit |
| CN205174394U (en) * | 2015-12-07 | 2016-04-20 | 天津商业大学 | Small -size burning furnace temperature measuring device that burns |
| CN205426522U (en) * | 2016-02-01 | 2016-08-03 | 浙江大学 | Heating of aeroengine blade flies disconnected device based on local heating principle |
| CN106289734A (en) * | 2016-07-21 | 2017-01-04 | 浙江大学 | A kind of aero-engine casing high temperature containment test technology |
| CN106839771A (en) * | 2017-02-23 | 2017-06-13 | 中国航发沈阳发动机研究所 | A kind of vertical rotor heating apparatus and system |
| CN207123169U (en) * | 2017-09-13 | 2018-03-20 | 河钢股份有限公司 | A kind of special heating furnace for fatigue at high temperature test |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020252983A1 (en) * | 2019-06-20 | 2020-12-24 | 浙江大学 | Material performance testing system under fixed multi-field coupling action in supergravity environment |
| US11609165B2 (en) | 2019-06-20 | 2023-03-21 | Zhejiang University | Material performance testing system under fixed multi-field coupling effect in hypergravity environment |
| CN112014110A (en) * | 2020-07-31 | 2020-12-01 | 中国航发贵阳发动机设计研究所 | Temperature field control device of vertical wheel disc low-cycle fatigue tester |
| CN112179661A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Heating device for wheel disc test |
| CN112179661B (en) * | 2020-09-18 | 2022-04-22 | 中国航发四川燃气涡轮研究院 | Heating device for wheel disc test |
| CN114136640A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Online adjustable gradient heating device for strength test of aero-engine wheel disc |
| CN114593606A (en) * | 2022-03-17 | 2022-06-07 | 中国航发沈阳发动机研究所 | A split vertical rotor heating device |
| CN116046195A (en) * | 2023-04-03 | 2023-05-02 | 中国航发四川燃气涡轮研究院 | Movable type aeroengine wheel disk temperature measuring device |
| FR3152881A1 (en) * | 2023-09-13 | 2025-03-14 | Safran Aircraft Engines | Self-retracting thermocouple for test bench |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109798771A (en) | One kind testing heating device for aero-engine turbine disk low cycle fatigue life | |
| CN110261216B (en) | Material performance testing system under supergravity environment suspension type multi-field coupling effect | |
| US11609165B2 (en) | Material performance testing system under fixed multi-field coupling effect in hypergravity environment | |
| CN109632886B (en) | Fine thermal assessment test system and method for high-speed aircraft cabin | |
| CN102288497B (en) | Heating device for Hopkinson pressure bar test | |
| CN101929969B (en) | Thermal contact resistance testing device with cooling device | |
| CN110243181B (en) | High-temperature heating device for testing mechanical properties of materials in hypergravity environment | |
| CN115165337B (en) | Turbine blade rotation thermal-mechanical fatigue test device and method | |
| CN106289734B (en) | A kind of aero-engine casing high temperature containment test technology | |
| CN106839771B (en) | A kind of vertical rotor heating apparatus and system | |
| CN208223987U (en) | Hot environment case for split hopkinson press bar experimental rig | |
| CN111929016A (en) | Heating furnace and high-temperature high-cycle fatigue test device | |
| CN105928972B (en) | Temperature measurement system and method inside and outside a kind of cable and cable bridge fireproof protective device | |
| CN206095591U (en) | Machine casket high temperature contains test device based on contact heating method | |
| CN111721641A (en) | A heating and constant temperature device and method for uniaxial compression test of high temperature rock | |
| US4357305A (en) | Coal gasification vessel | |
| CN103267636B (en) | For the heating arrangement of aero-engine spindle thermal state strength test | |
| KR101164057B1 (en) | Measuring device of insulation for thermal barrier coating using furnace | |
| KR20140010626A (en) | Spent fuel integrity test facility under accelerator condition | |
| CN210922175U (en) | A high-temperature heating device for testing the mechanical properties of materials in a hypergravity environment | |
| CN103869848B (en) | Sheet coupon torture test heating furnace | |
| JP2777822B2 (en) | Method and apparatus for testing thermal conductivity of non-planar heat insulating material | |
| JP2013519888A (en) | Temperature controller for thermal analysis test | |
| CN205982147U (en) | Vertical a plurality of big sample high temperature thermal dilatometer | |
| CN114487007B (en) | Assembled steel frame device capable of replacing fireproof test components and testing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 |
Application publication date: 20190524 |
|
| RJ01 | Rejection of invention patent application after publication |