CN113567133B - Device and method for testing low cycle fatigue of casing - Google Patents
Device and method for testing low cycle fatigue of casing Download PDFInfo
- Publication number
- CN113567133B CN113567133B CN202010350231.0A CN202010350231A CN113567133B CN 113567133 B CN113567133 B CN 113567133B CN 202010350231 A CN202010350231 A CN 202010350231A CN 113567133 B CN113567133 B CN 113567133B
- Authority
- CN
- China
- Prior art keywords
- casing
- temperature
- cycle fatigue
- air flow
- stress
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 40
- 238000012360 testing method Methods 0.000 title claims description 38
- 238000010438 heat treatment Methods 0.000 claims abstract description 99
- 238000009661 fatigue test Methods 0.000 claims abstract description 69
- 239000012530 fluid Substances 0.000 claims abstract description 63
- 238000011068 loading method Methods 0.000 claims description 70
- 238000001514 detection method Methods 0.000 claims description 14
- 238000001816 cooling Methods 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims description 6
- 238000009673 low cycle fatigue testing Methods 0.000 claims 2
- 230000001276 controlling effect Effects 0.000 description 6
- 239000011229 interlayer Substances 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a low-cycle fatigue test device and method for a casing, relates to the field of aeroengines, and is used for optimizing the low-cycle fatigue test of the casing. The low-cycle fatigue test device for the casing comprises a fixed clamp, a casing, a heating unit, a first airflow introduction flow passage and a second airflow introduction flow passage. The fixed clamp is used for providing support; the casing is fixedly connected with the fixed clamp; the casing is provided with a fluid inlet and a fluid outlet; the heating unit surrounds the outer side of the casing; the heating unit comprises a plurality of heating elements, and at least two heating elements are independent; the first air flow introducing flow passage is communicated with the fluid inlet of the casing. The second air flow introducing flow passage is communicated with the fluid inlet of the casing and is independent from the first air flow introducing flow passage. According to the technical scheme, the low cycle fatigue test of the casing is optimized.
Description
Technical Field
The invention relates to the field of aeroengines, in particular to a method and a device for testing low cycle fatigue of a casing.
Background
The aeroengine case simultaneously bears gas load, temperature load, inertial load, vibration load and the like, and the loading condition is quite complex. According to domestic and foreign statistics, most of the accidents of the casing are caused by fatigue, and the service life of the casing is usually determined based on a fatigue life test of the full-size casing.
The inventor finds that in the related art, the aero-engine case fatigue test can only apply normal temperature and temperature uniformity to one key part to simulate a stress state. An aeroengine case fatigue test can only make a definite life for a key part. If more than one key position is determined, a plurality of aero-engine case fatigue tests are planned for life determination. If other parts are damaged before the preset key parts in the test process, the fatigue test of the aeroengine casing needs to be redesigned, which consumes great labor cost, time cost and economic cost.
The inventors found that at least the following problems exist in the prior art: the existing low-cycle fatigue test method for the aero-engine casing cannot simulate the temperature field and the stress field of the whole casing, if a plurality of key parts are to be tested, a plurality of fatigue test schemes are required to be planned to determine the fatigue life of the casing, and the existing test process consumes great labor cost, time cost and economic cost.
Disclosure of Invention
The invention provides a device and a method for testing low cycle fatigue of a casing, which are used for optimizing the low cycle fatigue test of the casing.
The invention provides a low-cycle fatigue test device for a casing, which is characterized by comprising the following components:
a stationary fixture for providing support;
and one end of the casing switching section is connected with the fixed clamp and the loading clamp, and the other end of the casing switching section is connected with the casing and is used for simulating the rigidity, the casing installation state and the boundary conditions of the adjacent casings.
The casing is connected with the casing switching section; the casing is provided with a fluid inlet and a fluid outlet; a heating unit surrounding the outside of the casing; the heating unit comprises a plurality of heating elements, and at least two heating elements are independent;
a first air flow introduction flow passage in communication with a fluid inlet of the casing; and
a second airflow introduction flow passage communicates with the fluid inlet of the casing and is independent of the first airflow introduction flow passage.
In some embodiments, the heating element is annular, and a plurality of the heating elements are surrounded side by side on the outside of the casing.
In some embodiments, the plurality of heating elements are arranged from one axial end of the casing to the other axial end of the casing.
In some embodiments, the fluid inlet of the casing comprises two, a first fluid inlet and a second fluid inlet, respectively; the first fluid inlet communicates with the first air flow introduction flow passage and the second fluid inlet communicates with the second air flow introduction flow passage.
In some embodiments, the case low cycle fatigue test device further comprises:
a first gas source for providing a gas flow; and
a heating system in communication with the first air source and the first air stream introduction flow passage; the heating system is configured to heat the gas delivered by the first gas source and deliver the heated gas to the first gas flow introduction flow passage.
In some embodiments, the case low cycle fatigue test device further comprises:
a second gas source for providing a gas flow; and
a cooling system in communication with the second air source and the second air flow introduction flow passage; the heating system is configured to cool the gas delivered from the second gas source and deliver the cooled gas to the second gas flow introduction flow passage.
In some embodiments, the case low cycle fatigue test device further comprises:
the guide plate surrounds the outer side of the casing;
the first airflow introducing flow passage is positioned in a gap between the guide plate and the casing, and the second airflow introducing flow passage is positioned at the outer side of the guide plate.
In some embodiments, the case low cycle fatigue test device further comprises:
an axial load loading device is coupled to the casing, the axial load loading device configured to provide an axial load to the casing.
In some embodiments, the case low cycle fatigue test device further comprises:
and a lateral load loading device connected with the casing, wherein the lateral load loading device is configured to provide lateral load to the casing.
In some embodiments, the case low cycle fatigue test device further comprises:
a torque loading device is coupled to the casing, the torque loading device configured to provide torque to the casing.
In some embodiments, the case low cycle fatigue test device further comprises:
the temperature detection element is arranged on the casing so as to collect the temperature of the casing; and/or the number of the groups of groups,
the stress detection element is arranged on the casing so as to collect the stress of the casing.
The embodiment of the invention also provides a low cycle fatigue test method for the casing, which comprises the following steps:
determining a temperature profile and a stress profile of a set position of the casing;
according to the temperature profile and the stress profile, the service life of the computer case is calculated; finding out the cycle causing the greatest damage, and taking the cycle as a standard cycle;
determining the arrangement position of the heating unit according to the temperature distribution of the casing corresponding to the standard cycle peak point state;
determining respective fluid parameters of the first airflow introduction flow channel and the second airflow introduction flow channel according to stress distribution of the casing corresponding to the standard circulation peak point state;
and adjusting the heating performance of the heating unit, parameters of the first airflow introduction flow channel and the second airflow introduction flow channel, and carrying out a loading cycle fatigue test.
In some embodiments, adjusting the heating performance of the heating unit comprises:
and controlling the temperature of each heating element from one end to the other end along the axial direction of the casing.
In some embodiments, the fluid parameters of the first gas flow introduction flow channel include fluid temperature and fluid pressure; and/or, the fluid parameters of the second air flow introducing flow channel comprise fluid temperature and fluid pressure.
In some embodiments, prior to performing the load cycle fatigue test, further comprising the steps of: and controlling the axial load loading parameter.
In some embodiments, prior to performing the load cycle fatigue test, further comprising the steps of: and controlling the transverse load loading parameters.
In some embodiments, prior to performing the load cycle fatigue test, further comprising the steps of: controlling the torque load loading parameter.
In some embodiments, the case low cycle fatigue test method further comprises the steps of:
setting a temperature detection element at a set position of the casing to acquire temperature distribution of the casing;
judging whether the temperature field under the test condition of the casing is close to the temperature field under the condition of the casing engine according to the acquired temperature distribution;
if not, the temperature of each heating element of the heating unit is adjusted so that the temperature field under test conditions for the set position of the casing is close to the temperature field under engine conditions.
In some embodiments, the case low cycle fatigue test method further comprises the steps of:
setting a stress detection element at a set position of the casing to acquire stress distribution of the casing;
judging whether the stress field under the test condition of the set position of the case is close to the stress field under the condition of the engine according to the collected stress distribution;
and if the stress field is not close to the stress field under the test condition of the set position of the case and the stress field under the engine condition are close to each other by adjusting the fluid parameters of the first airflow introducing flow channel or the second airflow introducing flow channel.
In some embodiments, the life of the case according to the temperature profile and the stress profile includes: and obtaining standard circulation of the set position by adopting a damage rain flow counting method according to the temperature profile and the stress profile and the service life of the computer case.
According to the low-cycle fatigue test device for the casing, provided by the technical scheme, the test device comprises the heating unit which is provided with the plurality of heating pieces, and each heating piece is independent. And the test device is provided with a first airflow introducing flow passage and a second airflow introducing flow passage which are relatively independent, and high-temperature and low-temperature airflows can be simultaneously introduced into the casing according to the requirements. According to the technical scheme, the operation of the heating unit, the parameters of the first airflow introduction flow channel and the parameters of the second airflow introduction flow channel can be independently controlled, and the temperature field of the whole casing can be simulated through the combined action of the adjustable heating unit and the airflow. According to the technical scheme, through optimized heat transfer analysis, the combined action mode of the adjustable heating unit and the multi-path air flow is designed to simulate the temperature field of the whole aero-engine casing, so that the low-cycle fatigue test of the traditional aero-engine casing is replaced, the cold state or hot state test of the aero-engine casing in the traditional sense is broken through, a brand-new loading method for the low-cycle fatigue test of the aero-engine casing is provided, a new idea is opened up for the low-cycle fatigue test of the aero-engine casing, and test times, labor cost, time cost and economic cost are saved.
Further, the stress field of the whole aeroengine case can be simulated by the combined action of the adjustable mechanical load and the air flow. Finally, the required test load parameters in the testing process of the casing are determined. According to the technical scheme, a brand-new low cycle fatigue test method for the aero-engine casing is realized, and a cold state or hot state test of key parts of the aero-engine casing in the traditional sense is broken through. According to the technical scheme, the temperature field and the stress field of the whole casing are simulated, so that the analysis service lives of a plurality of key parts are verified through only one casing low-cycle fatigue test, the service life of the whole casing is determined, the low-cycle fatigue test of the aero-engine casing is optimized, and the cold state or hot state test of the aero-engine casing in the traditional sense is broken through.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a low cycle fatigue test device for a casing according to an embodiment of the present invention;
FIG. 2 is a schematic flow chart of a method for testing low cycle fatigue of a casing according to an embodiment of the present invention;
fig. 3 is a control schematic diagram of a low cycle fatigue test method for a casing according to an embodiment of the present invention.
Detailed Description
The technical scheme provided by the invention is described in more detail below with reference to fig. 1 to 3.
Referring to fig. 1, the embodiment of the invention provides a low-cycle fatigue test device for a casing, which is used for carrying out low-cycle fatigue test on an aeroengine casing and a casing 2 with similar structure and performance, and can be widely applied to aeroengine casing tests of military and civil aeroengines.
Referring to fig. 1, an embodiment of the present invention provides a low cycle fatigue test device for a casing, which includes a fixing clamp 1, a casing 2, a heating unit 3, a first air flow introduction flow passage 4, and a second air flow introduction flow passage 5.
Referring to fig. 1, a fixing jig 1 is used to provide support, and the fixing jig 1 is fixed with a base or the like. After one end of the casing 2 is mounted with the fixing clamp 1, the other end of the casing 2 is suspended, i.e. after the mounting is completed, the casing 2 is cantilever-shaped. The casing 2 is the test object. The wall of the casing 2 may be single-layered, double-layered with an interlayer cavity or a partial region of the casing 2 wall with an interlayer cavity.
Referring to fig. 1, the casing 2 is provided with a fluid inlet 21 and a fluid outlet 22. The fluid inlet 21 is for receiving fluid introduced from the first air flow introduction flow passage 4 and the second air flow introduction flow passage 5. The fluid inlet 21 of the casing 2 comprises two, a first fluid inlet 21a and a second fluid inlet 21b, respectively; the first fluid inlet 21a communicates with the first air flow introducing flow passage 4, and the second air flow introducing flow passage 5 communicates with the second air flow introducing flow passage 5. The first air flow introducing flow passage 4 and the second air flow introducing flow passage 5 are two independent flow passages, and one of the first air flow introducing flow passage 4 and the second air flow introducing flow passage 5 is used for introducing high-temperature fluid into the casing 2, and the other is used for introducing low-temperature fluid into the casing 2.
Specifically, the first air flow introduction flow passage 4 communicates with the fluid inlet 21 of the casing 2. The second air flow introduction flow passage 5 communicates with the fluid inlet 21 of the casing 2 and is independent from the first air flow introduction flow passage 4. For the double-layer structure of the wall body of the casing 2, the first air flow introducing flow passage 4 and the second air flow introducing flow passage 5 can also convey fluid into the interlayer cavity. The first air flow introduction flow passage 4 is used, for example, for introducing a preheated air flow into the interior of the casing 2, and the second air flow introduction flow passage 5 is used, for example, for introducing a cold air flow into the interior of the casing 2. The preheated air flows through the first opening 101 of the fixing clamp 1, flows through the heating elements 31 with different temperatures, is introduced into the casing 2, and flows out through the fluid outlet 22 of the casing 2. The cold air flow is introduced into the interior of the casing 2 through the second opening 102 of the fixing clip 1, through the third opening 103 of the deflector 10, and out through the fluid outlet 22 of the casing 2.
Referring to fig. 1, a heating unit 3 surrounds the outside of the casing 2. The heating unit 3 comprises a plurality of heating elements 31, at least two heating elements 31 being independent. The installation position of the heating unit 3 is designed to be adjustable in order to try to make the temperature distribution to which the casing 2 is subjected during the simulation identical to the temperature distribution during the actual operation of the casing 2. The heating element 31 is independent, meaning that the temperature of the heating element 31 is independently controlled. The specific arrangement modes are various, for example, for an aeroengine casing of a certain model, the temperature field is relatively determined, and the temperature field shows the temperature distribution rule of the casing 2. According to the temperature distribution law, a plurality of heating elements 31 with the same temperature are taken as a whole and are controlled uniformly. The heating elements 31 having different temperatures are separately controlled. The above manner can more precisely control the parameters of each heating unit 3, so that the temperature field of the casing 2 is more consistent with the temperature distribution condition of the actual aero-engine casing 2.
Referring to fig. 1, in some embodiments, the heating element 31 is annular, and a plurality of heating elements 31 are surrounded side by side on the outside of the casing 2. By providing a plurality of heating elements 31 in a row, a plurality of areas outside the casing 2 are provided with corresponding heating elements 31, and by controlling the temperature of the heating elements 31, the temperature distribution of the casing 2 can be controlled approximately.
With continued reference to fig. 1, in some embodiments, a plurality of heating elements 31 are arrayed from one axial end of the casing 2 to the other axial end of the casing 2. The heating element 31 is arranged such that the entire axial length of the casing 2 is covered by the heating element 31, so that the temperature field of the casing 2 can be controlled more precisely.
According to the technical scheme, the heating unit 3 is used for realizing the approximate temperature distribution of the casing, and the heating unit 3, the first airflow introducing flow passage 4 and the second airflow introducing flow passage 5 are matched together to realize more accurate temperature distribution.
Referring to fig. 1, in some embodiments, the case low cycle fatigue test apparatus further comprises a first gas source 6 and a heating system 7. The first air source 6 is for providing an air flow. The heating system 7 is communicated with the air source and the first air flow introducing flow passage 4; the heating system 7 is configured to heat the gas supplied from the first gas source 6 and then supply the heated gas to the first gas flow introducing flow passage 4. The gas output by the first gas source 6 is changed into high-temperature gas flow after passing through the heating system 7, and the high-temperature gas flow is subsequently introduced into the casing 2 to simulate the temperature field and the stress field of the casing 2.
With continued reference to FIG. 1, in some embodiments, the receiver low cycle fatigue test apparatus further includes a second air source 8 and a cooling system 9. The second air supply 8 is used to provide an air flow. The cooling system 9 is communicated with the air source and the second air flow introducing flow passage 5; the heating system 7 is configured to cool the gas supplied from the first gas source 6 and then supply the cooled gas to the second gas flow introducing flow passage 5. The gas output by the second gas source 8 is changed into low-temperature gas flow after passing through the cooling system 9, and the low-temperature gas flow is subsequently introduced into the casing 2 to simulate the temperature field and the stress field of the casing 2.
The first air source 6 and the second air source 8 may use the same air source. The flow from the air source is split into two branches, one branch flowing to the heating system 7 and the first air flow introduction flow passage 4, and the other branch flowing to the cooling system 9 and the second air flow introduction flow passage 5.
With continued reference to fig. 1, in some embodiments, the low cycle fatigue test apparatus further includes a baffle 10, the baffle 10 surrounding the exterior side of the casing 2. Wherein the first air flow introducing flow passage 4 is located in the gap between the baffle 10 and the casing 2, and the second air flow introducing flow passage 5 is located outside the baffle 10. The baffle 10 is configured in a ring shape, one end of the baffle 10 is fixed with the fixing jig 1, and the other end of the baffle 10 is fixed with the loading jig 17. The axial load loading means 11, the transverse load loading means 12 and the torque loading means 13, which will be described later, are located outside the area of the deflector 10, i.e. they are fixed to the side of the loading clamp 17 remote from the deflector 10. The first air source 6, the second air source 8, the heating system 7 and the cooling system 9 described above are located outside the area of the baffle 10, i.e. they are fixed to the side of the fixture 1 remote from the baffle 10.
According to the technical scheme, the temperature field of the whole casing 2 is simulated through the combined action mode of the adjustable heating unit 3, the preheating airflow and the cold airflow.
Referring to fig. 1, in some embodiments, the case low cycle fatigue test device further includes an axial load loading device 11, the axial load loading device 11 being coupled to the case 2, the axial load loading device 11 being configured to provide an axial load to the case 2. An axial load loading device 11 is mounted at the other end of the casing 2. The axial load loading means 11 is for example an actuator cylinder.
In some embodiments, the case low cycle fatigue test device further comprises a lateral load loading device 12 coupled to the case 2, the lateral load loading device 12 configured to provide lateral load to the case 2. A lateral load loading device 12 is mounted at the other end of the casing 2. The lateral load loading means 12 is for example an actuator cylinder. The lateral load loading means 12 are separated from the axial load loading means 11. Specifically, the casing 2 is charged with hydraulic red oil by hydraulic servo control to simulate the high-pressure compressor casing pressure distribution and axial load.
Referring to fig. 1, in some embodiments, the case low cycle fatigue test device further includes a torque loading device 13 coupled to the case 2, the torque loading device 13 configured to provide torque to the case 2. The torque loading device 13 is mounted at the other end of the casing 2. The torque loading means 13 is for example a ram. The lateral load loading means 12, the axial load loading means 11 and the torque loading means 13 are mutually separated.
Referring to fig. 1, in some embodiments, one end of a casing 2 is fixed with a fixing jig 1 by the fixing jig 1. The other end of the casing 2 is fixed with a casing switching section 16, and the casing switching section 16 is fixed with a loading clamp 17. The axial load loading means 11, the transverse load loading means 12 and the torque loading means 13 are all mounted to a loading jig 17.
In some embodiments, the case low cycle fatigue test device further comprises a temperature detection element 14 and/or a stress detection element 15. The temperature detecting element 14 is disposed on the casing 2 to collect the temperature of the casing 2. The stress detection element 15 is disposed on the casing 2 to collect stress distribution of the casing 2.
Each key part of the wall surface of the aero-engine case 2 needs to be provided with a sufficient number of temperature detecting elements 14 and stress detecting elements 15 as required. The temperature sensor is used as the temperature detecting element 14, and the strain gauge is used as the stress detecting element 15. According to the technical scheme, the temperature sensor of the temperature detection element 14 and the stress detection element 15 are respectively arranged at different positions of the wall surface of the aero-engine casing according to the actual temperature distribution and the actual stress distribution of the engine to monitor the temperature field and the stress field of the aero-engine casing in real time, and the respective air flow temperatures, air flow rates and mechanical loads of the heating unit 3, the first air flow introduction flow passage 4 and the second air flow introduction flow passage 5 are regulated through the closed loop control system so as to achieve the temperature field and the stress field required by the test. According to the technical scheme, through designing an integral heating and pressurizing mode, the temperature field and the stress field of the aero-engine casing are simulated more accurately, and further the service life of the high-pressure compressor is determined through an aero-engine casing fatigue test.
Referring to fig. 2 and 3, a method for testing low cycle fatigue of a casing is described below, which may be implemented by using the apparatus for testing low cycle fatigue of a casing provided in any of the foregoing embodiments. The low cycle fatigue test method of the casing comprises the following steps:
step S100, determining a temperature profile and a stress profile of the set position of the casing 2.
The set position refers to a key part obtained according to calculation and analysis.
The temperature profile refers to the temperature time history of a certain position of the casing; the temperature field is the temperature distribution of the casing 2 at a certain moment.
The stress profile refers to the stress time history of a certain position of the casing; the stress field is the stress distribution of the casing 2 at a certain moment.
Step S200, the service life of the set position of the computer case 2 is calculated according to the temperature profile and the stress profile, and the cycle causing the greatest damage is found out and used as the standard cycle.
In step S200, a cycle with the greatest damage is calculated by using a damage rain flow method according to the temperature profile and the stress profile. The damaged rain flow method is a counting method using a stress strain hysteresis loop as one cycle, compared with the rain flow counting method. This method is named because it looks like a rain stream flowing down from the top of the column. Standard rain flow counting breaks down the stress profile into a number of stress cycles based on the equivalent stress profile. And calculating damage of every two points according to the stress profile and the temperature profile by using the damage rain flow counting method, and selecting the largest damage circulation. And then converting the stress state of the peak point in the maximum damage cycle to an octahedron to obtain octahedral shearing stress, then projecting all six stress components of other state points to the octahedral shearing stress direction, and then carrying out standard rain flow counting on the octahedral shearing stress to obtain each cycle.
Step S300, determining the arrangement position of the heating unit 3 according to the temperature distribution of the casing corresponding to the standard cycle peak point state. Determining the arrangement positions of the heating units 3 refers to determining the number of settings, the pitch, which heating members 31 are to be controlled in common, and the like of the heating members 31 of the respective heating units 3. If precise temperature control is to be achieved, the above step S300 may also be combined with the adjustment of the respective fluid parameters of the first air flow introduction flow channel 4 and the second air flow introduction flow channel 5 described later to simulate the required temperature field.
And step 400, determining respective fluid parameters of the first air flow introducing flow channel 4 and the second air flow introducing flow channel 5 according to the stress distribution of the casing corresponding to the standard cycle peak point state.
The fluid parameters of the first air flow introduction flow passage 4 include the fluid temperature and the fluid pressure. The fluid parameters of the second air flow introduction flow channel 5 include the fluid temperature and the fluid pressure.
And S500, adjusting the heating performance of the heating unit 3 and parameters of the first airflow introduction flow channel 4 and the second airflow introduction flow channel 5, and carrying out a loading cycle fatigue test.
In step S500 described above, adjusting the heating performance of the heating unit 3 includes: the respective temperatures of the respective heating elements 31 along the axial direction of the casing 2 from one end to the other are controlled.
In some embodiments, prior to performing the load cycle fatigue test, further comprising the steps of: the axial load loading parameters of the axial load loading device 11 are controlled. The axial load loading means 11 is for example an actuator cylinder.
In some embodiments, prior to performing the load cycle fatigue test, further comprising the steps of: the lateral load loading parameters of the lateral load loading means 12 are controlled. The lateral load loading means 12 is for example an actuator cylinder.
In some embodiments, prior to performing the load cycle fatigue test, further comprising the steps of: the torque load loading parameter of the torque loading means 13 is controlled. The torque loading means 13 is for example a ram.
The order of execution steps of controlling the axial load loading parameter, the transverse load loading parameter and the torque load loading parameter is not particularly required, and the steps can be performed simultaneously or step by step. The load adjustment operation may also be coordinated with the above-described step of determining the respective fluid parameters of the first and second air flow introduction channels 4, 5 to simulate the required stress field.
In some embodiments, the case low cycle fatigue test method further comprises the steps of:
step one, a temperature detecting element 14 is arranged at a set position of the casing 2 to collect temperature distribution of the casing 2.
And step two, judging whether the temperature field under the test condition of the casing 2 is close to the temperature field under the engine condition of the casing 2 according to the acquired temperature distribution.
And step three, if the temperature of each heating element 31 of the heating unit 3 is not close, the temperature field of the set position of the case 2 under test conditions is adjusted to be close to the temperature field of the set position of the engine.
Through the steps, closed loop feedback of temperature distribution can be realized, so that the temperature field born by the casing 2 is the same as the temperature field under the condition of the engine as much as possible in the test process.
In some embodiments, the case low cycle fatigue test method further comprises the steps of:
step one, a stress detection element 15 is disposed at a set position of the casing 2 to collect stress distribution of the casing 2.
And step two, judging whether the stress field of the set position of the case 2 under the test condition is close to the stress field of the engine condition according to the acquired stress distribution.
And step three, if the stress fields are not similar, adjusting the fluid parameters of the first airflow introducing flow channel 4 or the second airflow introducing flow channel 5 so that the stress field under the test condition of the set position of the casing 2 is similar to the stress field under the engine condition.
Through the steps, closed loop feedback of stress distribution can be realized, so that the stress field born by the casing 2 is the same as the stress field under the condition of the engine as much as possible in the test process.
Referring to fig. 1 to 3, some specific implementations of the case low cycle fatigue test method are described below.
The control system 18 is in communication with the heating unit 3, the heating system 7, the cooling system 9, the axial load loading device 11, the transverse load loading device 12, the torque loading device 13, the temperature detecting element 14, and the stress detecting element 15.
Before the test starts, simulation calculation is performed on the case 2 of the aeroengine, and key positions of possible failure of the case 2 are determined through stress analysis, heat transfer analysis, service life analysis and safety analysis results.
Firstly, determining the temperature profile of each key part of the casing 2 according to heat transfer analysis under different engine states; and determining the stress profile of each key part of the casing 2 according to stress analysis under different engine states.
And secondly, calculating the service life according to the temperature profile and the stress profile of each key part, finding out the cycle causing the greatest damage by using a damage rain flow method, and taking the cycle as a standard cycle.
Again, the arrangement of the heating elements 31 is designed according to the temperature profile of the standard cycle, and the temperature and spacing of each heating element 31 is adjustable to approximately achieve the temperature profile of the standard cycle. The first air flow introducing flow passage 4 and the second air flow introducing flow passage 5 are designed according to the pressure distribution of the standard circulation, and the pressure and the temperature of the cold and hot air flow are respectively adjustable to realize the pressure distribution of the casing 2. The cold and hot air flow can also adjust the temperature distribution so as to realize more accurate temperature distribution; the arrangement of the rams is designed to achieve axial forces, torque and lateral forces in accordance with the mechanical load of a standard cycle.
Repeatedly, sticking temperature sensors and strain gauges on the inner and outer surfaces of the casing 2 to measure the temperature distribution and stress distribution of the casing 2, and feeding back the result to a control system, wherein the control system adjusts the temperature of each heating element 31 and the temperature of cold and hot air flow to finally reach the temperature field of the standard cycle of the engine; the control system finally reaches the standard cyclic stress field of the engine by respectively adjusting the pressure of the cold and hot air flow and the load of the actuator cylinder.
Finally, the load cycle fatigue test was performed with the final adjusted air flow pressure and temperature of each path, the temperature of each heating element 31, and the load of each actuator.
In the description of the present invention, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the protection of the present invention.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may be modified or some technical features may be replaced with others, which may not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (17)
1. The utility model provides a quick-witted casket low cycle fatigue test device which characterized in that includes:
a stationary fixture (1) for providing support;
the casing (2) is fixedly connected with the fixed clamp (1); the casing (2) is provided with a fluid inlet (21) and a fluid outlet (22);
a heating unit (3) surrounding the outside of the casing (2); the heating unit (3) comprises a plurality of heating elements (31), at least two of the heating elements (31) being independent;
a first air flow introduction flow passage (4) communicating with a fluid inlet (21) of the casing (2); and
a second air flow introduction flow passage (5) communicating with the fluid inlet (21) of the casing (2) and being independent of the first air flow introduction flow passage (4);
wherein the temperature field of the case is simulated by the combined action of the heating unit (3) and the air flow by independently controlling the operation of the heating unit (3), the parameters of the first air flow introducing flow channel (4) and the parameters of the second air flow introducing flow channel (5);
wherein, the low cycle fatigue test device of receiver still includes:
-an axial load loading device (11) connected to the casing (2), the axial load loading device (11) being configured to provide an axial load to the casing (2);
a lateral load loading device (12) connected to the casing (2), the lateral load loading device (12) being configured to provide a lateral load to the casing (2);
a torque loading device (13) connected to the casing (2), the torque loading device (13) being configured to provide torque to the casing (2);
wherein the stress field of the whole aeroengine casing is simulated by adjusting the combined action of the axial load loading device (11), the transverse load loading device (12), the torque loading device (13) and the air flow.
2. The case low cycle fatigue test device according to claim 1, wherein the heating member (31) is ring-shaped, and a plurality of the heating members (31) are surrounded side by side on the outside of the case (2).
3. The casing low cycle fatigue test device according to claim 1, wherein a plurality of the heating elements (31) are arranged from one axial end of the casing (2) to the other axial end of the casing (2).
4. The casing low cycle fatigue test device according to claim 1, wherein the fluid inlet (21) of the casing (2) comprises two, a first fluid inlet (21 a) and a second fluid inlet (21 b), respectively; the first fluid inlet (21 a) communicates with the first air flow introduction flow passage (4), and the second fluid inlet (21 b) communicates with the second air flow introduction flow passage (5).
5. The receiver low cycle fatigue test device of claim 1, further comprising:
a first air source (6) for providing an air flow; and
a heating system (7) in communication with the first gas source (6) and the first gas flow introduction flow passage (4); the heating system (7) is configured to heat the gas delivered by the first gas source (6) and deliver the heated gas to the first gas flow introduction flow passage (4).
6. The receiver low cycle fatigue test device according to claim 5, further comprising:
a second air source (8) for providing an air flow; and
a cooling system (9) in communication with said second air supply (8) and said second air flow introduction flow passage (5); the heating system (7) is configured to cool the gas delivered by the second gas source (8) and deliver it to the second gas flow introduction flow passage (5).
7. The receiver low cycle fatigue test device of claim 1, further comprising:
the guide plate (10) surrounds the outer side of the casing (2);
wherein the first air flow introducing flow passage (4) is positioned in a gap between the guide plate (10) and the casing (2), and the second air flow introducing flow passage (5) is positioned outside the guide plate (10).
8. The receiver low cycle fatigue test device of claim 1, further comprising:
a temperature detection element (14) which is arranged on the casing (2) so as to collect the temperature of the casing (2); and/or the number of the groups of groups,
and the stress detection element (15) is arranged on the casing (2) so as to collect the stress of the casing (2).
9. A method for testing low cycle fatigue of a casing, which is characterized by being implemented by the device for testing low cycle fatigue of a casing according to any one of claims 1 to 8, comprising the following steps:
determining a temperature profile and a stress profile of a set position of the casing;
according to the temperature profile and the stress profile, the service life of the set position of the computer case is calculated, and the cycle causing the greatest damage is found out and used as the standard cycle;
determining the arrangement position of the heating unit according to the temperature distribution of the casing corresponding to the standard cycle peak point state;
determining respective fluid parameters of the first airflow introduction flow channel and the second airflow introduction flow channel according to stress distribution of the casing corresponding to the standard circulation peak point state;
and adjusting the heating performance of the heating unit, parameters of the first airflow introduction flow channel and the second airflow introduction flow channel, and carrying out a loading cycle fatigue test.
10. The receiver low cycle fatigue test method according to claim 9, wherein adjusting the heating performance of the heating unit comprises:
and controlling the temperature of each heating element from one end to the other end along the axial direction of the casing.
11. The method of claim 9, wherein the fluid parameters of the first air flow introduction flow path include fluid temperature and fluid pressure; and/or, the fluid parameters of the second air flow introducing flow channel comprise fluid temperature and fluid pressure.
12. The method of claim 9, further comprising the step of, prior to performing the load cycle fatigue test:
and controlling the axial load loading parameter.
13. The method of claim 9, further comprising the step of, prior to performing the load cycle fatigue test:
and controlling the transverse load loading parameters.
14. The method of claim 9, further comprising the step of, prior to performing the load cycle fatigue test:
controlling the torque load loading parameter.
15. The method for low cycle fatigue testing of a receiver according to claim 9, further comprising the steps of:
setting a temperature detection element at a set position of the casing to acquire temperature distribution of the casing;
judging whether the temperature field under the test condition of the casing is close to the temperature field under the engine condition of the casing according to the acquired temperature distribution;
if not, the temperature of each heating element of the heating unit is adjusted so that the temperature field under test conditions for the set position of the casing is close to the temperature field under engine conditions.
16. The method for low cycle fatigue testing of a receiver according to claim 9, further comprising the steps of:
setting a stress detection element at a set position of the casing to acquire stress distribution of the casing;
judging whether the stress field under the test condition of the set position of the case is close to the stress field under the condition of the engine according to the collected stress distribution;
and if the stress field is not close to the stress field under the test condition of the set position of the case and the stress field under the engine condition are close to each other by adjusting the fluid parameters of the first airflow introducing flow channel or the second airflow introducing flow channel.
17. The method of claim 9, wherein calculating the life of the case based on the temperature profile and the stress profile comprises:
and obtaining standard circulation of the set position by adopting a damage rain flow counting method according to the temperature profile and the stress profile and the service life of the computer case.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010350231.0A CN113567133B (en) | 2020-04-28 | 2020-04-28 | Device and method for testing low cycle fatigue of casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010350231.0A CN113567133B (en) | 2020-04-28 | 2020-04-28 | Device and method for testing low cycle fatigue of casing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113567133A CN113567133A (en) | 2021-10-29 |
| CN113567133B true CN113567133B (en) | 2024-04-12 |
Family
ID=78158042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010350231.0A Active CN113567133B (en) | 2020-04-28 | 2020-04-28 | Device and method for testing low cycle fatigue of casing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113567133B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526919A (en) * | 2022-02-21 | 2022-05-24 | 中国航发贵阳发动机设计研究所 | Test method and tool for verifying strength of special-shaped jet pipe of aircraft engine |
| CN116046408A (en) * | 2022-09-09 | 2023-05-02 | 中国航发沈阳发动机研究所 | Loading determination and testing method for fatigue test of turbine rear casing structural parts |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6209390B1 (en) * | 1999-05-14 | 2001-04-03 | Larue Gerald Duane | Turbocharger fatigue life monitor |
| CN101793619A (en) * | 2010-03-12 | 2010-08-04 | 北京理工大学 | Test bench with double combustion chambers, double superchargers and low cycle fatigue based on self-circulation mode |
| CN102053039A (en) * | 2010-12-07 | 2011-05-11 | 浙江大学 | Engine body hydraulic fatigue test system |
| CN102866007A (en) * | 2012-09-20 | 2013-01-09 | 潍柴动力股份有限公司 | Cylinder head fatigue test device and method |
| JP2015132555A (en) * | 2014-01-14 | 2015-07-23 | 三菱重工業株式会社 | Thermal fatigue test apparatus |
| CN106840643A (en) * | 2017-04-06 | 2017-06-13 | 中国科学院工程热物理研究所 | The measurement apparatus of casing thermal deformation under a kind of impingement heat transfer |
| CN206515272U (en) * | 2016-11-09 | 2017-09-22 | 吉林大学 | Thermograde controlled burning bullet |
| CN206557029U (en) * | 2017-01-13 | 2017-10-13 | 西北工业大学 | One kind rotation air film cooled thermograde thermal mechanical fatigue pilot system |
| CN109030012A (en) * | 2018-08-24 | 2018-12-18 | 哈尔滨电气股份有限公司 | A kind of turbine blade root fatigue test simulating piece and test method with cooling duct |
-
2020
- 2020-04-28 CN CN202010350231.0A patent/CN113567133B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6209390B1 (en) * | 1999-05-14 | 2001-04-03 | Larue Gerald Duane | Turbocharger fatigue life monitor |
| CN101793619A (en) * | 2010-03-12 | 2010-08-04 | 北京理工大学 | Test bench with double combustion chambers, double superchargers and low cycle fatigue based on self-circulation mode |
| CN102053039A (en) * | 2010-12-07 | 2011-05-11 | 浙江大学 | Engine body hydraulic fatigue test system |
| CN102866007A (en) * | 2012-09-20 | 2013-01-09 | 潍柴动力股份有限公司 | Cylinder head fatigue test device and method |
| JP2015132555A (en) * | 2014-01-14 | 2015-07-23 | 三菱重工業株式会社 | Thermal fatigue test apparatus |
| CN206515272U (en) * | 2016-11-09 | 2017-09-22 | 吉林大学 | Thermograde controlled burning bullet |
| CN206557029U (en) * | 2017-01-13 | 2017-10-13 | 西北工业大学 | One kind rotation air film cooled thermograde thermal mechanical fatigue pilot system |
| CN106840643A (en) * | 2017-04-06 | 2017-06-13 | 中国科学院工程热物理研究所 | The measurement apparatus of casing thermal deformation under a kind of impingement heat transfer |
| CN109030012A (en) * | 2018-08-24 | 2018-12-18 | 哈尔滨电气股份有限公司 | A kind of turbine blade root fatigue test simulating piece and test method with cooling duct |
Non-Patent Citations (4)
| Title |
|---|
| 发动机零件的低循环疲劳寿命消耗和循环换算率;王通北等;航空发动机(第1期);第10-18页 * |
| 直升机尾减速器机匣疲劳试验方法研究;张勇等;材料开发与应用;第31卷(第6期);第22-27页 * |
| 航空发动机寿命分析与监测方法;葛治美等;航空发动机;第32卷(第1期);第25-28页 * |
| 航空发动机综合飞行换算率的确定;徐可君等;推进技术;第27卷(第1期);第24-29页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113567133A (en) | 2021-10-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113567133B (en) | Device and method for testing low cycle fatigue of casing | |
| CN107421984B (en) | A kind of hollow turbine vane is superimposed the thermal mechanical fatigue pilot system and method for high Zhou Zhendong | |
| CN106644702B (en) | A kind of high temperature fatigue test clamp and method of continuously adjustable blade examination stress distribution | |
| CN109253940A (en) | A kind of experimental provision for turbo blade material heat fatigue | |
| EP2354783A1 (en) | Thermal inspection system and method incorporating external flow | |
| CN101424666A (en) | Method and apparatus for testing and evaluating machine components under simulated in-situ thermal operating conditions | |
| CN104458574B (en) | Device and method for testing shear strength in ultrahigh-temperature or large-temperature-difference environment | |
| CN107091734A (en) | A kind of cylinder head thermal fatigue test apparatus | |
| CN109580209A (en) | A kind of alternating-current generator of airplane combustion oil cooler service life experimental testers | |
| CZ299500B6 (en) | Method and apparatus for testing thermal fatigue of cylinder head of internal combustion engine and calibration method thereof | |
| CN107860785A (en) | A kind of quick thermal fatigue test method of engine cylinder cap and device | |
| CN112665864A (en) | Device and method for simulating random thermal shock load of aircraft engine | |
| CN104374864B (en) | Propellant burning velocity testing device under a kind of extended state | |
| KR101517217B1 (en) | Total monitoring system for injection mold | |
| CN109292113B (en) | Temperature control thermostat testing device and testing method | |
| CN112706943A (en) | Aircraft internal and external heat source coupling test device and test method | |
| CN109060578B (en) | Thermal fatigue testing device for cylinder cover of diesel engine | |
| CN113484020B (en) | Thermal power coupling test device for simulating high-temperature service environment of aircraft engine | |
| CN109959572A (en) | Temperature is with measurement and test of mechanical properties of metal device and method under stress dynamic linkage environment | |
| CN109030012A (en) | A kind of turbine blade root fatigue test simulating piece and test method with cooling duct | |
| US20170038092A1 (en) | Method for adjusting a heating system, exhaust measuring device, and adjustment arrangement | |
| CN110736671B (en) | Method for monitoring abnormal part of pipe fitting hardness | |
| CN113865874A (en) | Sealing ring testing machine with air pressure loading function | |
| CN207457110U (en) | A kind of quick thermal fatigue test apparatus of engine cylinder cap | |
| CN116990150A (en) | Ceramic matrix composite flame tube temperature difference thermal cycle device and reliability evaluation 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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |