CN114720123A - Novel vertical combustion engine main shaft static force and fatigue test device - Google Patents
Novel vertical combustion engine main shaft static force and fatigue test device Download PDFInfo
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- CN114720123A CN114720123A CN202210239057.1A CN202210239057A CN114720123A CN 114720123 A CN114720123 A CN 114720123A CN 202210239057 A CN202210239057 A CN 202210239057A CN 114720123 A CN114720123 A CN 114720123A
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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
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/027—Test-benches with force-applying means, e.g. loading of drive shafts along several directions
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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
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
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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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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The utility model belongs to the aviation field, in particular to novel vertical combustion engine main shaft static and fatigue test device, design a novel vertical combustion engine static and fatigue test device, this test device can simulate the constraint condition of combustion engine axle to exert axial force, moment of torsion (including steady state moment of torsion and vibration moment of torsion), moment of flexure (including rotatory moment of flexure) simultaneously to the oar axle, satisfy the intensity examination demand of each type of combustion engine axle, and this technique can also be applied to the intensity test of other main shafts class, has the commonality.
Description
Technical Field
The application belongs to the field of gas turbines, and particularly relates to a novel vertical gas turbine main shaft static force and fatigue test device.
Background
The main shaft of the gas turbine plays an important role, and plays a role in transmitting power and supporting at the same time. As a main bearing component and a special rotating part of the gas turbine, the working environment of the main shaft is high in rotating speed, high in temperature and high in pressure, is filled with lubricant and has certain corrosivity. The loads experienced by the main shaft are very complex, including centrifugal loads, operating torque (and vibration torque), gyroscopic moments, moments of inertia, and temperature loads, as well as composite loads between them. In addition, since the spindle is mounted with a high-speed rotating member, the spindle is also subjected to a vibration stress. The main shaft generates low-cycle cyclic fatigue damage by the working torque and the axial force, the main shaft generates high-cycle cyclic fatigue damage by the gyro moment, the inertia moment and the vibration torque, and the thermal stress is generated on the main shaft by the temperature load.
In order to improve the reliability of the gas turbine, it is necessary to test the static strength and fatigue life of the gas turbine main shaft. The main loads for the hydrostatic and fatigue tests are: axial force, torque and bending moment of one or more bending moment assessment sections. The torque in the fatigue test is further divided into steady-state working torque and vibration torque, and in the same high-cycle period, the bending moment of the examination section needs to rotate 360 degrees around the shaft, and the rotation directions are the same.
The existing vertical spindle static force and fatigue test device (the test device is suitable for the spindle strength test of an aeroengine, and the spindle strength test of a combustion engine is not carried out).
The axial force load acts on the fan shaft and the rear shaft neck of the low-pressure turbine shaft through an axial force loading measuring assembly (an acting cylinder, a dynamometer and a switching tool) through an axial line, the main shaft is in a hollow structural form, and the load is fed back by the dynamometer on the axial force loading measuring assembly.
The torque load (the torque in the fatigue test is also divided into steady-state working torque and vibration torque) is respectively acted on the fan shaft and the rear shaft neck of the low-pressure turbine shaft through a torque loading measuring component (an action cylinder, a dynamometer and a switching tool) and a torque bearing component (the action cylinder and the switching tool), and the load is measured by a torque meter on the torque loading measuring component.
The bending moment is through moment loading measurement component, and it includes: the actuating cylinder, the dynamometer and the adapter tooling act on the rear shaft neck of the low-pressure turbine shaft in the form of transverse force. In the static test, a set of bending moment loading measurement assembly applies load to the low-pressure turbine shaft, and the load value is determined by the bending moment value on the examination section, the axial distance between the action center of the transverse force of the added bending moment and the No.5 fulcrum; in the fatigue test, two sets of bending moment loading and measuring assemblies which are 90 degrees to each other on the action section of the transverse force of the bending moment are used for applying load, the load waveforms of the two sets of bending moment loading and measuring assemblies are sine wave curves with the phase difference of 90 degrees, and the average value is 0, so that the action effect that the transverse force of the bending moment in the fatigue test also rotates around the shaft is realized.
Disclosure of Invention
In order to solve the above problems, the present application provides a novel vertical combustion engine mainshaft static and fatigue test device, as shown in the schematic diagram in the first drawing, which includes:
a main shaft to be tested, which is provided with a fan shaft at the front end and a low-pressure turbine shaft at the rear end;
a torque loading measurement assembly coupled to an outer surface of the fan shaft;
the axial force loading measuring component is coaxially connected with the torque loading measuring component;
the fixed end assembly is integrally disc-shaped and is provided with outer ring mounting holes and inner ring mounting holes which are distributed along the circumferential direction in an array mode, the outer ring mounting holes and the adjacent inner ring mounting holes are located on the same radius line, and the included angle degree between the adjacent radius lines is a common divisor of 120 degrees;
the center of a circle of one end face of the fixed end assembly is connected with an axial force loading measuring assembly, a cylindrical connector is installed in the inner ring installation hole on the same end face, and the connector is connected with the low-pressure turbine shaft; and the other end surface of the fixed end component is provided with a single lug seat component through the outer ring mounting hole and the adjacent inner ring mounting hole, each single lug seat component is connected with a bending moment loading and measuring component, and different bending moment loading and measuring components enable the fixed end component to incline by providing axial forces in different directions, so that the fixed end component provides bending moment for the low-pressure turbine shaft through the connector.
Preferably, the single ear mount assembly to which the fixed end assembly is mounted includes a first connection means and a second connection means, and the first connection means includes: the fixed end assembly is provided with two single-lug seat assemblies at an interval of 180 degrees, and each single-lug seat assembly is connected with a bending moment loading measurement assembly; the second connection mode: the device comprises three single-lug seat assemblies which are arranged at intervals of 120 degrees at fixed end assemblies, wherein each single-lug seat assembly is connected with a bending moment loading measurement assembly.
Preferably, the fixed end assembly includes: the cover plate is disc-shaped, and a recess for accommodating the bottom plate is arranged in the middle of the cover plate.
Preferably, the side of the fixed end assembly has a support assembly connected to a post fixed to the ground, the support assembly limiting the radial sliding movement of the fixed end assembly.
Preferably, a No.4 fulcrum transverse force loading measuring assembly is installed at the position of the low-pressure turbine shaft, and the No.4 fulcrum transverse force loading measuring assembly is provided with a cylinder and is connected with a stand column fixed on the ground.
Preferably, the fixed end assembly is connected with the axial force loading measuring assembly at the circle center of one end face through a hinge joint, and the fixed end assembly has three-direction rotational freedom degrees.
The advantages of the present application include:
1. a novel torque load bearing and measuring structure is designed, and the occupied space is small;
2. a brand-new rotating bending moment loading measurement structure is designed, the component can apply bending moment in any direction, the number of tools is small, and the processing cost is low;
3. a novel rotary bending moment loading method is adopted, bending moment is applied through the inclination of the disc-shaped assembly, pure bending moment can be loaded by the method, and additional transverse force is not brought to the main shaft;
4. the bending moment is provided by adopting the form of the fixed end assembly, and the pure bending moment and the rotating bending moment test can be realized by the same device.
Drawings
FIG. 1 is a schematic diagram of a novel vertical combustion engine mainshaft static and fatigue testing device according to a preferred embodiment of the application;
FIG. 2 is a schematic view of a first connection of the fixed end assembly (9);
FIG. 3 is a cross-sectional view of a first connection of the fixed end assembly (9);
FIG. 4 is a schematic view of a second connection of the fixed end assembly (9);
FIG. 5 is a bending moment calculation equivalent mechanical model using the apparatus of the present application;
wherein, 1-torque loading measurement assembly; 2-axial force loading measuring assembly; 3-No.2 fulcrum support assembly; 4-No.4 fulcrum transverse force loading measurement assembly; 5-a main shaft; 6-a connector; 7-No.5 fulcrum support assembly; 8-bending moment loading measurement component; 9-a fixed end assembly; 91-a cover plate; 92-a single ear mount assembly; 93-bottom plate.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making creative efforts shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a novel static and fatigue test of vertical combustion engine main shaft device includes:
the experimental device mainly applies force under a real environment to the fan shaft and the low-pressure turbine shaft so as to realize that each mechanical effect of the main shaft reaches an allowable standard;
the torque loading measuring component 1 is connected with the outer surface of the fan shaft and is used for actually applying torque to the fan shaft, and a corresponding torque bearing device is arranged at the position of a low-pressure turbine shaft;
the axial force loading measuring component 2 is coaxially connected with the torque loading measuring component 1;
the fixed end assembly 9 is integrally disc-shaped and is provided with outer ring mounting holes and inner ring mounting holes which are distributed in an array mode along the circumferential direction, the outer ring mounting holes and the adjacent inner ring mounting holes of the outer ring mounting holes are located on the same radius line, and the included angle degree between the adjacent radius lines is a common divisor of 120 degrees, so that the installation position of the bending moment loading and measuring assembly 8 can be guaranteed to be maintained, and pure bending moment and rotation bending moment can be provided;
the center of a circle of one end face of the fixed end component 9 is connected with the axial force loading measuring component 2, a cylindrical connector 6 is installed in the inner ring installation hole on the same end face, and the connector 6 is connected with the low-pressure turbine shaft; the other end face of the fixed end assembly 9 is provided with a single lug seat assembly 92 through the outer ring mounting hole and the adjacent inner ring mounting hole, each single lug seat assembly 92 is connected with a bending moment loading measuring assembly 8, the different bending moment loading measuring assemblies 8 enable the fixed end assembly 9 to incline by providing axial forces in different directions, and therefore the fixed end assembly 9 provides bending moment for the low-pressure turbine shaft through the connector 6.
In some alternative embodiments, the single ear mount assembly 92 to which the fixed end assembly 9 is attached includes a first attachment means, as shown in FIG. 2 and FIG. 3, and a second attachment means, as shown in FIG. 4, the first attachment means includes: two single-lug seat assemblies 92 with 180-degree intervals are arranged on the fixed end assembly 9, and each single-lug seat assembly 92 is connected with a bending moment loading measurement assembly 8; the second connection mode: the device comprises three single-lug seat assemblies 92 with intervals of 120 degrees, wherein each single-lug seat assembly 92 is connected with a bending moment loading measurement assembly 8.
In some alternative embodiments, the fixed end assembly 9 comprises: the cover plate 91 is in a disc shape, and the cover plate 91 has a recess for accommodating the base plate 93.
In some alternative embodiments, the sides of the fixed end assembly 9 have a support assembly to which a post fixed to the ground is attached that limits the fixed end assembly 9 from sliding in a radial direction.
In some alternative embodiments, a No.4 fulcrum transverse force loading measuring assembly 4 is installed at the low-pressure turbine shaft, and the No.4 fulcrum transverse force loading measuring assembly 4 is provided with a ram cylinder and is connected with a stand column fixed on the ground.
In some alternative embodiments, the axial force loading measuring assembly 2 is connected at the center of one end face of the fixed end assembly 9 through a hinge, and the fixed end assembly 9 has three-directional rotational freedom degrees.
The following tests can be realized by applying the device of the application:
1. axial force
The axial force load is loaded on the measuring component through the axial force, the measuring component is provided with an acting cylinder, a force sensor and a switching tool, the axial force load acts on the low-pressure shaft and the rear shaft neck of the low-pressure turbine shaft through the axis, the main shaft is in a hollow structural form, and the load is fed back by a dynamometer on the axial force load measuring component.
2. Torque of
The torque load is applied to the main shaft through the torque loading measuring assembly, the torque bearing assembly is connected with the low-pressure turbine disc, and the load is measured by a torque meter on the torque loading measuring assembly.
3. Bending moment
The bending moment is applied to the low-pressure turbine disc by a bending moment loading measuring assembly (consisting of a fixed end assembly and a force load loading measuring assembly) through a torque bearing assembly, so that a pure bending load is applied to the main shaft; the bending moment applied to the low-pressure turbine disc is applied by a force load loading assembly in the bending moment loading measurement assembly, and the magnitude of the bending moment is determined by the bending moment of an examination section.
3.1 static test
A fixed end assembly of the bending moment loading measurement assembly in the static test is shown in fig. 3 and comprises a cover plate, a single lug seat assembly and a bottom plate, wherein the cover plate is fixed with a test platform, the bottom plate is arranged between the cover plate and the platform and can be fixed at any angular position, the single lug seat assembly is fixed on the bottom plate, and the other end of the single lug seat assembly is connected with two sets of force load loading measurement assemblies which are 180 degrees from each other. Axial loads with equal magnitude and opposite directions can be applied to the low-pressure turbine disc, so that pure bending loads are applied to the main shaft, and the load value is determined by the bending moment value on the examination section, the action center of the bending moment on the low-pressure turbine disc and the axial distance between the No.5 fulcrum.
3.2 fatigue test
The bending moment loading measuring component (and the fixed end part of the platform) in the fatigue test is shown as 4, three sets of force load loading measuring components which are 120 degrees mutually act on the low-pressure turbine disc to apply rotating bending moment, the load waveforms of the three sets of loading measuring components are sine wave curves (the mean value is 0, and the amplitude value can be calculated by the formula (1)) with the phase difference of 120 degrees, and the action effect of the bending moment rotating around the shaft in the fatigue test is realized;
3.3 method for calculating bending moment
The main shaft of the gas turbine can be simplified into a two-fulcrum supporting structure, an equivalent mechanical model is shown in figure 5, and a relational expression of an examination section and bending moment applied to a low-pressure turbine disc can be established;
a) when the bending moment evaluation section is between the No.2 fulcrum and the low-pressure turbine disc, namely L is more than or equal to 02, examination of≤L2, lowThe bending moment generated by each load at the bending moment assessment section is as follows:
in the formula: mExaminationThe bending moment of the cross section is examined by the bending moment required by the test task, N.m;
MbendThe bending moment load measuring assembly is used for measuring the bending moment N.m generated on the low-pressure turbine disc.
b) When the bending moment test section is between the low-pressure turbine disc and the No.5 fulcrum, namely L2, low≤L2, examination of
≤L2,5The bending moment generated by each load at the bending moment assessment section is as follows:
force load calculation method in 3.4 bending moment loading assembly
M can be obtained from the expressions (1) and (2)BendAnd further, the force load in the bending moment loading assembly is obtained.
a) Static test
The M is applied by two sets of force load loading measurement components which are 180 degrees from each otherBendThe load value is:
in the formula: fz-force load loading the force load applied by the measuring assembly, N;
r-radius of the circle of the position of the single ear seat component in the fixed end component, m.
b) Fatigue test
M is applied by three sets of force load loading measurement components which are 120 degrees mutuallyBendWhen the rotating direction of the bending moment synthesized by loading the wave curves is clockwise along the forward-looking low-pressure turbine rotor in order to enable the bending moment to rotate around the main shaft, the mathematical expression of each path of force load loading measurement component is shown in a formula (4); when the rotation direction of the bending moment synthesized by the loading waveform curve is along the anticlockwise direction of the forward-looking low-pressure turbine rotor, the mathematical expression of each path of force load loading measurement component is shown in a formula (5); and substituting the formula (3) into the formula (I), so that the applied force load required by the force load loading measurement assembly can be solved:
in the formula: omega-fatigue test load frequency, unit: hz;
t-time, unit: and s.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A novel vertical combustion engine main shaft static and fatigue test device comprises:
the main shaft to be tested comprises a fan shaft at the front end and a low-pressure turbine shaft at the rear end;
a torque load measuring assembly (1) connected to the outer surface of the fan shaft;
an axial force loading measuring component (2) coaxially connected with the torque loading measuring component (1);
it is characterized by also comprising:
the fixed end assembly (9) is integrally disc-shaped and is provided with outer ring mounting holes and inner ring mounting holes which are distributed along the circumferential direction in an array mode, the outer ring mounting holes and the adjacent inner ring mounting holes are located on the same radius line, and the included angle degree between the adjacent radius lines is a common divisor of 120 degrees;
the center of a circle of one end face of the fixed end assembly (9) is connected with the axial force loading measuring assembly (2), a cylindrical connector (6) is installed in the inner ring installation hole in the same end face, and the connector (6) is connected with the low-pressure turbine shaft; and the other end surface of the fixed end assembly (9) is provided with a single lug seat assembly (92) through the outer ring mounting hole and the adjacent inner ring mounting hole thereof, each single lug seat assembly (92) is connected with a bending moment loading and measuring assembly (8), and different bending moment loading and measuring assemblies (8) enable the fixed end assembly (9) to incline by providing axial forces in different directions, so that the fixed end assembly (9) provides bending moment for the low-pressure turbine shaft through the connector (6).
2. A novel vertical combustion engine mainshaft static and fatigue testing apparatus as claimed in claim 1, characterised in that the fixed end assembly (9) is mounted on a single trunnion mount assembly (92) comprising a first connection means and a second connection means, the first connection means comprising: two single-lug seat assemblies (92) with 180-degree intervals are mounted on the fixed end assembly (9), and each single-lug seat assembly (92) is connected with a bending moment loading measurement assembly (8); the second connection mode: the three-lug-seat type bending moment load measuring device comprises three single-lug-seat assemblies (92) which are installed at intervals of 120 degrees on a fixed end assembly (9), wherein each single-lug-seat assembly (92) is connected with a bending moment load measuring assembly (8).
3. A new vertical combustion engine mainshaft static and fatigue testing apparatus according to claim 1, characterised in that the fixed end assembly (9) comprises: the cover plate (91) is disc-shaped, and a recess for accommodating the bottom plate (93) is arranged in the middle of the cover plate (91).
4. A novel vertical type combustion engine spindle static and fatigue test device according to claim 1, characterized in that the side of the fixed end assembly (9) is provided with a support assembly, the support assembly is connected with a stand column fixed on the ground, and the support assembly limits the radial sliding of the fixed end assembly (9).
5. The novel vertical type combustion engine main shaft static and fatigue test device according to claim 1, characterized in that a No.4 fulcrum transverse force loading measurement assembly (4) is installed at the low-pressure turbine shaft and is connected with a stand column fixed on the ground for providing a transverse force for the low-pressure turbine shaft.
6. A novel vertical type combustion engine main shaft static force and fatigue test device according to claim 1, characterized in that the center of a circle of one end face of the fixed end component (9) is connected with the axial force loading measuring component (2) through a hinge joint, and the fixed end component (9) has three-direction rotational freedom degrees.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210239057.1A CN114720123A (en) | 2022-03-11 | 2022-03-11 | Novel vertical combustion engine main shaft static force and fatigue test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210239057.1A CN114720123A (en) | 2022-03-11 | 2022-03-11 | Novel vertical combustion engine main shaft static force and fatigue test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117054229A (en) * | 2023-10-12 | 2023-11-14 | 中海油田服务股份有限公司 | Fixing device and method for testing reliability of circuit board of logging while drilling instrument |
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2022
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117054229A (en) * | 2023-10-12 | 2023-11-14 | 中海油田服务股份有限公司 | Fixing device and method for testing reliability of circuit board of logging while drilling instrument |
| CN117054229B (en) * | 2023-10-12 | 2023-12-19 | 中海油田服务股份有限公司 | Fixing device and method for testing reliability of circuit board of logging while drilling instrument |
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