CN116046408A - Loading determination and testing method for fatigue test of turbine rear casing structural parts - Google Patents
Loading determination and testing method for fatigue test of turbine rear casing structural parts Download PDFInfo
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- CN116046408A CN116046408A CN202211104907.3A CN202211104907A CN116046408A CN 116046408 A CN116046408 A CN 116046408A CN 202211104907 A CN202211104907 A CN 202211104907A CN 116046408 A CN116046408 A CN 116046408A
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- 238000012360 testing method Methods 0.000 title claims abstract description 73
- 238000009661 fatigue test Methods 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 claims abstract description 35
- 238000004088 simulation Methods 0.000 claims abstract description 11
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The application relates to a method for determining and testing fatigue test loading of a turbine rear casing structure part, wherein the method for determining the fatigue test loading of the turbine rear casing structure part comprises the following steps: in the design state, performing fatigue simulation analysis on the rear casing structure of the turbine to obtain stress distribution of the rear casing structure of the turbine in the design state; determining a fatigue key assessment part of the rear casing structure of the turbine according to the stress distribution of the rear casing structure of the turbine in a design state; in the test state of the parts, performing fatigue simulation analysis on the rear case structure of the turbine to obtain stress distribution of the rear case structure of the turbine in the test state of the parts; and (3) adjusting the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part, so that the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the test state of the part is consistent with that of the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the design state, and correspondingly obtaining the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part.
Description
Technical Field
The application belongs to the technical field of fatigue tests of rear casing structures of turbines, and particularly relates to a loading determination and test method for fatigue tests of parts of rear casing structures of turbines.
Background
The rear casing structure of the turbine in the aeroengine mainly comprises an outer casing, an inner ring arranged in the outer casing, and a plurality of support plates distributed between the outer casing and the inner ring along the circumferential direction, wherein the outer casing is connected between the front casing and the outer culvert casing of the turbine, the inner ring is connected with a bearing seat through a switching structure, and a bearing is installed in the bearing seat for supporting.
The complex load of the turbine rear casing structure in the aero-engine when the aero-engine works, including pneumatic load, motor load and temperature load, is a key bearing component in the aero-engine, and can be used for carrying out fatigue test to verify the fatigue performance of the rear casing bearing structure, so that support can be provided for the structural design and improvement of the turbine rear casing.
Because the test device is separated from the aero-engine, the temperature field of the rear casing structure of the turbine is difficult to simulate under the condition of a laboratory, accurate temperature load is difficult to be applied to the rear casing structure of the turbine, the complete machine test verification of the aero-engine can truly reflect the temperature environment of the rear casing, however, the complete machine test verification period is long, the efficiency is low, and the actual requirements of the design and improvement of the rear casing structure of the turbine are difficult to be met.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a method for determining and testing fatigue test loading of a turbine rear casing structural part, so as to overcome or alleviate at least one technical defect existing in the prior art.
The technical scheme of the application is as follows:
on the one hand, the method for determining the fatigue test loading of the turbine rear casing structural part comprises the following steps:
in the design state, performing fatigue simulation analysis on the rear casing structure of the turbine to obtain stress distribution of the rear casing structure of the turbine in the design state;
determining a fatigue key assessment part of the rear casing structure of the turbine according to the stress distribution of the rear casing structure of the turbine in a design state;
in the test state of the parts, performing fatigue simulation analysis on the rear case structure of the turbine to obtain stress distribution of the rear case structure of the turbine in the test state of the parts;
and (3) adjusting the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part, so that the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the test state of the part is consistent with that of the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the design state, and correspondingly obtaining the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part.
According to at least one embodiment of the present application, in the method for determining fatigue test loading of a component of a rear casing structure of a turbine, in the component test state, a test load loading point on the rear casing structure of the turbine includes:
a front end surface of the inner ring, to which a pulling load F1 is applied forward in the axial direction;
the rear side of the switching structure is applied with a pressing loading load F2 axially forwards;
inside the bearing housing, a radially outward pressing load R5 is applied thereon.
According to at least one embodiment of the application, in the method for determining the fatigue test loading of the turbine rear casing structural part, in the part test state, the front end of the outer casing is provided with the switching end for position constraint.
According to at least one embodiment of the application, in the method for determining the fatigue test loading of the turbine rear casing structural part, under the test state of the part, the working conditions of stress distribution level of the fatigue key assessment part and similar loading load of the test load loading point are combined.
On the other hand, the fatigue test method for the parts of the rear casing structure of the turbine comprises the following steps:
and in the test state of the parts, loading the load at each test load loading point obtained by the fatigue test loading determining method of the parts of the rear case structure of the turbine.
According to at least one embodiment of the present application, in the method for testing fatigue of a structural part of a rear casing of a turbine, the method further includes:
when the fatigue analysis is carried out on the rear casing structure of the turbine, the material performance of the rear casing structure of the turbine is corrected based on the temperature difference of the design state and the test state of the parts.
Drawings
Fig. 1 is a schematic diagram of a method for determining fatigue test loading of a rear casing structural component of a turbine according to an embodiment of the present application;
fig. 2 is a schematic diagram of a fatigue test method for a rear casing structural component of a turbine according to an embodiment of the present application;
fig. 3 is a schematic diagram of load loading performed at a test load loading point on a turbine rear casing structure in a test state of a component provided in an embodiment of the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with figures 1 to 3.
On the one hand, a method for determining fatigue test loading of parts of a rear casing structure of a turbine is provided, referring to fig. 1, and comprises the following steps:
in the design state, the stress distribution of the rear casing structure of the turbine in the design state can be obtained by performing fatigue simulation analysis on the rear casing structure of the turbine in the complete machine state of the aero-engine;
determining a fatigue key checking part of the turbine rear casing structure according to the stress distribution of the turbine rear casing structure in a design state, wherein the fatigue key checking part comprises a connecting part between a support plate and an inner ring and an outer ring high-stress part;
in the test state of the parts, performing fatigue simulation analysis on the rear case structure of the turbine to obtain stress distribution of the rear case structure of the turbine in the test state of the parts;
and (3) adjusting the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part, so that the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the test state of the part is consistent with that of the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the design state, and correspondingly obtaining the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part.
For the method for determining the loading of the fatigue test of the parts of the rear casing structure of the turbine disclosed by the embodiment, it can be understood by those skilled in the art that the fatigue critical checking part is determined as a main concerned part based on the stress distribution of the fatigue simulation analysis of the rear casing structure of the turbine in the design state, and the loading of each test load loading point on the rear casing structure of the turbine, which is consistent with the stress distribution of the fatigue critical checking part of the rear casing structure of the turbine in the design state, is performed in the part test state, so as to be used as the loading load of each test load loading point on the rear casing structure of the turbine in the part test state, namely, the pneumatic load, the mechanical load and the temperature load which are received by the rear casing structure of the turbine when the aeroengine works are replaced by the force load simulation in the test state, and the fatigue test of the parts of the rear casing structure of the turbine is performed based on the stress distribution, so that the fatigue capacity of the rear casing structure of the turbine can be quickly and efficiently accurately obtained, and the support is provided for the design and improvement of the rear casing structure of the turbine.
In the method for determining the loading of the fatigue test of the parts of the rear casing structure of the turbine disclosed in the above embodiment, the judging standard of the stress distribution of the critical assessment part of the fatigue of the rear casing structure of the turbine in the test state of the parts and the design state of the parts can be set by relevant technicians according to specific actual practice when the technical scheme disclosed in the application is applied, and no more detailed description is made here.
In some optional embodiments, in the method for determining fatigue test loading of a part of a rear casing structure of a turbine, in the part test state, a test load loading point on the rear casing structure of the turbine is a key bearing part on the rear casing structure of the turbine, see fig. 3, including:
a front end surface of the inner ring, to which a pulling load F1 is applied forward in the axial direction;
the rear side of the switching structure is applied with a pressing loading load F2 axially forwards;
inside the bearing housing, a radially outward pressing load R5 is applied thereon.
In some optional embodiments, in the method for determining fatigue test loading of a part of the turbine rear casing structure, in the part test state, the front end of the outer casing is provided with a switching end for position constraint, that is, the front end supports the turbine rear casing structure.
In some optional embodiments, in the method for determining the fatigue test loading of the turbine rear casing structural component, in the component test state, the working conditions of stress distribution level of the fatigue key assessment part and similar loading load of the test load loading point are combined, so that the loading working condition of the fatigue test of the turbine rear casing structural component is reduced, and the workload is reduced.
In another aspect, a method for testing fatigue of a structural component of a rear casing of a turbine is provided, see fig. 2, including:
and in the test state of the parts, loading the load at each test load loading point obtained by the fatigue test loading determining method of the parts of the rear case structure of the turbine.
For the method for determining the fatigue test of the structural part of the rear casing of the turbine disclosed in the above embodiment, it can be understood by those skilled in the art that, because the method for determining the fatigue test load of the structural part of the rear casing of the turbine disclosed in the above embodiment is implemented, the description is simpler, the specific relevant points can be referred to the relevant description of the method for determining the fatigue test load of the structural part of the rear casing of the turbine, and the technical effects thereof can also be referred to the technical effects of the relevant parts of the method for determining the fatigue test load of the structural part of the rear casing of the turbine, which are not repeated herein.
In some optional embodiments, the method for testing fatigue of a structural part of a rear casing of a turbine further includes:
when the fatigue analysis is carried out on the rear casing structure of the turbine, the temperature difference of the design state and the test state of the parts can be specifically selected based on the temperature difference of the design state and the test state of the parts of the critical fatigue checking part, and the material performance of the rear casing structure of the turbine is corrected.
The method comprises the steps of carrying out load loading by using the loading load of each test load loading point obtained by the method for determining the fatigue test loading of the parts of the rear casing structure of the turbine disclosed by the embodiment under different temperature conditions, so that the pneumatic load, the mechanical load and the temperature load of the parts of the rear casing structure of the turbine, which are born by the rear casing structure of the turbine when the aircraft engine works, can be replaced by force load simulation under the test conditions, and the fatigue test of the parts of the rear casing structure of the turbine is carried out based on the pneumatic load, the mechanical load and the temperature load.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (6)
1. A method for determining fatigue test loading of a turbine rear casing structural part is characterized by comprising the following steps:
in the design state, performing fatigue simulation analysis on the rear casing structure of the turbine to obtain stress distribution of the rear casing structure of the turbine in the design state;
determining a fatigue key assessment part of the rear casing structure of the turbine according to the stress distribution of the rear casing structure of the turbine in a design state;
in the test state of the parts, performing fatigue simulation analysis on the rear case structure of the turbine to obtain stress distribution of the rear case structure of the turbine in the test state of the parts;
and (3) adjusting the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part, so that the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the test state of the part is consistent with that of the stress distribution of the critical fatigue checking part of the rear casing structure of the turbine under the design state, and correspondingly obtaining the loading load of each test load loading point on the rear casing structure of the turbine under the test state of the part.
2. The method for determining the fatigue test loading of the turbine rear casing structural component according to claim 1, wherein,
under the spare part test state, the structural test load loading point of machine casket behind the turbine includes:
a front end surface of the inner ring, to which a pulling load F1 is applied forward in the axial direction;
the rear side of the switching structure is applied with a pressing loading load F2 axially forwards;
inside the bearing housing, a radially outward pressing load R5 is applied thereon.
3. The method for determining the fatigue test loading of the turbine rear casing structural component according to claim 1, wherein,
and in the test state of the parts, the front end of the outer casing is provided with a switching end for position constraint.
4. The method for determining the fatigue test loading of the turbine rear casing structural component according to claim 1, wherein,
and under the test state of the parts, combining the working conditions of stress distribution level of the key fatigue checking part and similar loading load of the test load loading point.
5. A fatigue test method for parts of a rear casing structure of a turbine is characterized by comprising the following steps:
in the test state of the parts, loading loads of all test load loading points obtained by the fatigue test loading determining method of the parts of the rear case structure of the turbine according to any one of claims 1-4 are used for loading loads.
6. The method for fatigue testing a structural component of a rear case of a turbine according to claim 5, wherein,
further comprises:
when the fatigue analysis is carried out on the rear casing structure of the turbine, the material performance of the rear casing structure of the turbine is corrected based on the temperature difference of the design state and the test state of the parts.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211104907.3A CN116046408A (en) | 2022-09-09 | 2022-09-09 | Loading determination and testing method for fatigue test of turbine rear casing structural parts |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211104907.3A CN116046408A (en) | 2022-09-09 | 2022-09-09 | Loading determination and testing method for fatigue test of turbine rear casing structural parts |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106649990A (en) * | 2016-11-16 | 2017-05-10 | 中国北方发动机研究所(天津) | Engine main connecting rod load simplifying method applied to rapid fatigue test |
| CN110543666A (en) * | 2019-07-22 | 2019-12-06 | 中国航发北京航空材料研究院 | Method for testing low-cycle fatigue performance of component with hole structure |
| CN113567133A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Low-cycle fatigue test device and method for casing |
| CN113720707A (en) * | 2021-08-23 | 2021-11-30 | 中国飞机强度研究所 | Design method for large-deformation loading point of structural fatigue test |
| CN114492107A (en) * | 2021-12-30 | 2022-05-13 | 南京航空航天大学 | Fatigue test simulation piece design method for checking turbine disc rim convex block |
| CN114840931A (en) * | 2022-05-17 | 2022-08-02 | 中国航发沈阳发动机研究所 | Method for designing blade body strength simulation test piece of turbine blade of aero-engine |
-
2022
- 2022-09-09 CN CN202211104907.3A patent/CN116046408A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106649990A (en) * | 2016-11-16 | 2017-05-10 | 中国北方发动机研究所(天津) | Engine main connecting rod load simplifying method applied to rapid fatigue test |
| CN110543666A (en) * | 2019-07-22 | 2019-12-06 | 中国航发北京航空材料研究院 | Method for testing low-cycle fatigue performance of component with hole structure |
| CN113567133A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Low-cycle fatigue test device and method for casing |
| CN113720707A (en) * | 2021-08-23 | 2021-11-30 | 中国飞机强度研究所 | Design method for large-deformation loading point of structural fatigue test |
| CN114492107A (en) * | 2021-12-30 | 2022-05-13 | 南京航空航天大学 | Fatigue test simulation piece design method for checking turbine disc rim convex block |
| CN114840931A (en) * | 2022-05-17 | 2022-08-02 | 中国航发沈阳发动机研究所 | Method for designing blade body strength simulation test piece of turbine blade of aero-engine |
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Application publication date: 20230502 |