CN116519307A - Blade fixing structure for supersonic plane blade grid test and design method thereof - Google Patents
Blade fixing structure for supersonic plane blade grid test and design method thereof Download PDFInfo
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- CN116519307A CN116519307A CN202310733580.4A CN202310733580A CN116519307A CN 116519307 A CN116519307 A CN 116519307A CN 202310733580 A CN202310733580 A CN 202310733580A CN 116519307 A CN116519307 A CN 116519307A
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- blade
- grid plate
- shaped hole
- edge
- test
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- 238000000034 method Methods 0.000 title claims abstract description 25
- 239000000463 material Substances 0.000 claims abstract description 23
- 238000013016 damping Methods 0.000 claims abstract description 21
- 239000011358 absorbing material Substances 0.000 claims 2
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- G01M15/02—Details or accessories of testing apparatus
-
- 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
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application provides a blade fixing structure for supersonic plane blade cascade test and a design method thereof, which belong to the technical field of aeroengines, wherein the design method comprises the following steps: constructing grid plates with blade-shaped holes according to the blade shapes of the blades in the blade grid test, fixing the blades in the flow channel through the grid plates with the blade-shaped holes, and calculating stress concentration positions and ranges of the leading edges and the trailing edges of the blades; respectively rounding the front edge and the tail edge of the blade-shaped hole to obtain a rounded blade-shaped hole, thereby obtaining a grid plate for supporting the blade, wherein the circle centers of the rounded front edge and tail edge are positioned in a camber line of the blade shape; the method comprises the steps of placing a blade in a blade-shaped hole formed by rounding a grid plate, forming a gap between the blade and the blade-shaped hole formed by rounding, filling vibration damping material into the gap, enabling the vibration damping material to be leveled with the inner side surface of the grid plate on one side of a runner of the grid plate, enabling the vibration damping material to form a cylindrical part with larger diameter on the outer side of the runner of the grid plate, enabling the cylindrical part to be leveled and bonded with the outer side surface of the grid plate, and thus obtaining the cylindrical plug.
Description
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a blade fixing structure for a supersonic plane blade grid test and a design method thereof.
Background
The planar cascade test is a fundamental test of compressor blade and turbine blade designs in aeroengines and gas turbines. The planar cascade test allows independent investigation of some important parameters of the blade, thus accumulating a large amount of available practical reference data for the design of the engine blade.
With the improvement of aerodynamic loads and efficiency of fans/compressors and turbines, the Mach numbers of inlet and outlet of test pieces are higher and higher, and plane blade grid blowing tests in a supersonic range are more and more emphasized. Therefore, the reasonable design of the supersonic plane blade grid test piece is particularly important. One of the existing supersonic plane blade grid test pieces is to fix the blades in the flow channel by the left and right grid plates with blade holes, and for the blades with thinner front and rear edges, the fixing positions of the two ends of the fixed blades are often damaged in the test process.
To address the problem of blade damage, this is typically accomplished by increasing the chord length of the blade or releasing the blade from a fixed location where the stresses at the leading and trailing edges are greater. However, for the same tester, increasing the chord length of the blade can cause the reduction of the number of grid plate blades, the periodicity of the flow field is poor, and the test precision is adversely affected; and the front and rear edges of the blades are completely released into the flow field from the fixed position, so that the front and rear edges of the blades are greatly deformed.
Disclosure of Invention
The invention aims to provide a blade fixing structure for a supersonic plane blade grid test and a design method thereof, which are used for solving or alleviating at least one problem in the background technology.
The technical scheme of the application is as follows: the blade fixing structure design method for the supersonic plane blade grid test comprises the following steps:
constructing a grid plate with a blade-shaped hole according to the blade profile of the blade in a blade grid test, fixing the blade in a runner through the grid plate with the blade-shaped hole, calculating a stress field of the blade in a test state, and further determining stress concentration positions and ranges of the front edge and the tail edge of the blade according to the stress field;
for stress concentration areas near the front edge and the tail edge of the blade, respectively rounding the front edge and the tail edge of the blade-shaped hole to obtain a rounded blade-shaped hole, thereby obtaining a grid plate for supporting the blade, wherein the circle centers of the front edge and the tail edge rounding are positioned in a camber line of the blade profile;
the method comprises the steps that a blade is placed in a blade-shaped hole formed by rounding a grid plate, a gap is formed between the blade and the blade-shaped hole formed by rounding, vibration reduction materials are filled in the gap, the vibration reduction materials are leveled with the inner side surface of the grid plate on one side of a runner of the grid plate, the vibration reduction materials form a cylindrical part with larger diameter on the outer side of the runner of the grid plate, the cylindrical part is leveled and bonded with the outer side surface of the grid plate, and therefore a cylindrical plug is obtained, and the grid plate for supporting the blade and the cylindrical plug form a blade fixing structure.
In a preferred embodiment of the present application, the radius at which the leading and trailing edges of the blade-shaped holes are rounded is determined according to the extent of the stress concentration at the leading and trailing edges.
In a preferred embodiment of the present application, the connection position between the circles made by the front edge and the rear edge of the blade-shaped hole and the blade profile is rounded.
In a preferred embodiment of the present application, the vibration damping material comprises vibration damping rubber.
On the other hand, the technical scheme provided by the application is as follows: a blade securing structure for a supersonic planar cascade test, comprising:
the blade-shaped holes are formed by rounding the front edge and the tail edge of the blade-shaped holes, and the centers of circles of the front edge and the tail edge of the blade-shaped holes are positioned in the camber line of the blade shape; and
the cylindrical plug comprises a cylindrical part with a larger diameter and a plug part obtained by filling a gap between a blade and a rounded blade-shaped hole, wherein the plug part is internally provided with a matching part for adapting to the front edge and/or the tail edge profile of the blade, the end face of the plug part is leveled with the inner surface of one side of the grid plate runner, and the connecting surface of the cylindrical part and the plug part is leveled with the outer surface of the grid plate runner.
In a preferred embodiment of the present application, the circles made by the leading edge and the trailing edge of the blade-shaped hole are determined according to the positions and the ranges of stress concentration of the leading edge and the trailing edge of the blade in the test state, which are calculated according to the test performed in the flow channel by the blade arranged on the grid plate of the blade-shaped hole without the circles.
In a preferred embodiment of the present application, the cylindrical plug is made of vibration-damping material.
In a preferred embodiment of the present application, the vibration damping material comprises vibration damping rubber.
In a preferred embodiment of the present application, the attachment surface is adhesively bonded to the outer surface of the grid runner.
In a preferred embodiment of the present application, the adhesive is a removable soft gel.
The utility model provides a through set up circular structure at the front and back edge of the blade type hole of grid tray, through cylinder type end cap damping buffering in circular structure in order to solve supersonic speed plane cascade blade and take place to damage in the too big and the emergence of test in-process concentrated stress, reduce blade amplitude through the great damping coefficient of the cylinder type end cap of rubber material simultaneously to reduce the probability of fatigue damage in the blade test process, extension test blade's life.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a flow chart of a method of designing a blade fixing structure according to the present application.
FIG. 2 is a schematic view of the original grid structure of the present application.
FIG. 3 is a schematic view of the structure of the round grating plate in the present application.
FIG. 4 is a schematic view of a blade placed in a grid after rounding in the present application.
FIG. 5 is a schematic illustration of the location of the vibration damping material filling in the present application.
Fig. 6 is a schematic structural diagram of a cylindrical plug in the present application.
FIG. 7 is a schematic view of a blade securing structure in the present application.
Reference numerals:
10-grid plate
11-blade type hole
12-blade-shaped hole after rounding
20-blade test piece
30-vibration reduction plug
31-cylindrical portion
32-plug part
33-mating part
34-junction surface
35-end face
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, 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 order to solve the problem that the supersonic plane blade grid blade is damaged due to overlarge stress concentration in the test process, and meanwhile, the vibration amplitude of the blade in the test process is reduced, the application provides a blade fixing structure for the supersonic plane blade grid test and a design method thereof.
As shown in FIG. 1, the present application first provides a method for designing a blade fixing structure for supersonic planar cascade test, comprising the following steps:
step S1: according to the blade profile of the blade in the blade grid test, a grid plate with a blade-shaped hole is constructed, the blade is fixed in a runner through a left grid plate and a right grid plate with the blade-shaped hole, the stress field of the blade in the test state is calculated, and the stress concentration position and the stress concentration range of the front edge and the tail edge of the blade are further determined according to the stress field.
FIG. 2 illustrates a louver 10 according to an embodiment of the present application, wherein louver 10 has a blade-shaped aperture 11.
Step S2: for the stress concentration areas near the front edge and the tail edge of the blade, circles are respectively made on the front edge and the tail edge of the blade-shaped hole, and the circle center is positioned in the camber line, so that a supporting and fixing structure for fixing the blade is obtained. Wherein the radius of the leading and trailing edge rounding of the blade-shaped holes is determined according to the extent of the stress concentration of the leading and trailing edges.
Fig. 3 shows the blade-shaped holes 12 rounded at the leading and trailing edges of the blade-shaped holes of the louver 10 in the embodiment of the present application, wherein the connection points of the leading and trailing edges of the blade-shaped holes and the blade profile are rounded to reduce stress concentration.
And S3, placing the blades in the blade-shaped holes formed by rounding the grid plates to form a gap area, filling vibration damping materials into the gap area, wherein the vibration damping materials are leveled with the inner side surface of the grid plates on one side of the flow channels of the grid plates, the vibration damping materials form cylindrical parts with larger diameters on the outer side of the flow channels of the grid plates, and the cylindrical parts are leveled and bonded with the outer side surface of the grid plates, so that the vibration damping materials form the cylindrical plugs 30.
When the blade 20 is installed in the blade-shaped hole 12 formed by rounding the louver 10 as shown in fig. 4, the blade 20 and the blade-shaped hole 12 have gaps at the front and rear edges, and the gaps are filled with a vibration damping material, which may be a vibration damping rubber material as shown in fig. 5. The vibration-damping material may be solidified to form a cylindrical plug 30.
As shown in fig. 6, the cylindrical plug 30 in the present application is shown in a schematic structural diagram, where the cylindrical plug 30 includes a cylindrical portion 31 with a larger diameter and a plug portion 32 obtained by filling, and a mating portion 33 adapted to the profile of the leading edge or the trailing edge of the blade is provided in the plug portion 32, and an end face 35 of the plug portion 32 is leveled with a plane inside the flow channel of the grid plate 10, and a connection face 34 of the cylindrical portion 31 and the plug portion 32 is leveled with a plane outside the flow channel of the grid plate 10. Wherein the connection surface 34 can be adhered to the plane outside the flow channel of the grid plate 10 by bonding, and the bonding adopts detachable soft rubber.
As shown in fig. 7, the present application also provides a blade-fixing structure for supersonic planar cascade test, the blade-fixing structure comprising: left and right grid plates 10 and a cylindrical plug 30.
The left and right louvers 10 are symmetrical, and are described herein as either louver. The grid plate 10 is provided with a plurality of blade-shaped holes 11, the front edge and the tail edge of the blade-shaped holes 11 are rounded to obtain rounded blade-shaped holes 12, and the circle center is positioned on the camber line of the blade shape.
The circles in the round blade-shaped holes 12 are tested in the flow channel according to the blades arranged on the grid plates 10 of the round blade-shaped holes 11, and the calculated positions and ranges of stress concentration of the leading edge and the trailing edge of the blades in the test state are determined.
The cylindrical plug 30 includes a cylindrical portion 31 having a larger diameter and a plug portion 32 obtained by filling a gap between the blade 20 and the rounded blade-shaped hole 12, and the plug portion 32 has therein a fitting portion 33 for fitting the blade leading edge and/or trailing edge profile, and an end face 35 of the plug portion 32 is flush with a plane inside the flow passage of the louver 10, and a connection face 34 of the cylindrical portion 31 and the plug portion 32 is flush with a plane outside the flow passage of the louver 10. Wherein the connection surface 34 can be adhered to the plane outside the flow channel of the grid plate 10 by bonding, and the bonding adopts detachable soft rubber.
The utility model provides a through set up circular structure at the front and back edge of the blade type hole of grid tray, through cylinder type end cap damping buffering in circular structure in order to solve supersonic speed plane cascade blade and take place to damage in the too big and the emergence of test in-process concentrated stress, reduce blade amplitude through the great damping coefficient of the cylinder type end cap of rubber material simultaneously to reduce the probability of fatigue damage in the blade test process, extension test blade's life.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (10)
1. A method for designing a blade-fixing structure for a supersonic planar cascade test, the method comprising:
constructing a grid plate with a blade-shaped hole according to the blade profile of the blade in a blade grid test, fixing the blade in a runner through the grid plate with the blade-shaped hole, calculating a stress field of the blade in a test state, and further determining stress concentration positions and ranges of the front edge and the tail edge of the blade according to the stress field;
for stress concentration areas near the front edge and the tail edge of the blade, respectively rounding the front edge and the tail edge of the blade-shaped hole to obtain a rounded blade-shaped hole, thereby obtaining a grid plate for supporting the blade, wherein the circle centers of the front edge and the tail edge rounding are positioned in a camber line of the blade profile;
the method comprises the steps that a blade is placed in a blade-shaped hole formed by rounding a grid plate, a gap is formed between the blade and the blade-shaped hole formed by rounding, vibration reduction materials are filled in the gap, the vibration reduction materials are leveled with the inner side surface of the grid plate on one side of a runner of the grid plate, the vibration reduction materials form a cylindrical part with larger diameter on the outer side of the runner of the grid plate, the cylindrical part is leveled and bonded with the outer side surface of the grid plate, and therefore a cylindrical plug is obtained, and the grid plate for supporting the blade and the cylindrical plug form a blade fixing structure.
2. The blade holding structure design method for supersonic planar cascade test of claim 1, wherein the radius of the leading and trailing edge rounding of said blade-shaped holes is determined according to the extent of the stress concentration of the leading and trailing edges.
3. A method of designing a blade fixing structure for a supersonic planar cascade test according to claim 1 or 2, wherein the connection position of the circles made by the leading edge and the trailing edge of the blade-shaped hole and the blade-shaped line is rounded.
4. The blade holding structure design method for supersonic planar cascade test of claim 1, wherein said vibration absorbing material comprises vibration absorbing rubber.
5. A blade fixing structure for supersonic speed plane cascade test, its characterized in that, blade fixing structure includes:
the blade-shaped holes are formed by rounding the front edge and the tail edge of the blade-shaped holes, and the centers of circles of the front edge and the tail edge of the blade-shaped holes are positioned in the camber line of the blade shape; and
the cylindrical plug comprises a cylindrical part with a larger diameter and a plug part obtained by filling a gap between a blade and a rounded blade-shaped hole, wherein the plug part is internally provided with a matching part for adapting to the front edge and/or the tail edge profile of the blade, the end face of the plug part is leveled with the inner surface of one side of the grid plate runner, and the connecting surface of the cylindrical part and the plug part is leveled with the outer surface of the grid plate runner.
6. The blade fixing structure for supersonic planar cascade test according to claim 5, wherein the circles made by the leading edge and the trailing edge of the blade-shaped hole are determined according to the positions and the ranges of stress concentration of the leading edge and the trailing edge of the blade calculated by the test performed in the flow passage by the blade disposed on the louver of the blade-shaped hole without the circles in the test state.
7. The blade holding structure for supersonic planar cascade test of claim 5, wherein said cylindrical plug is made of vibration damping material.
8. The blade holding structure for a supersonic planar cascade test of claim 7, wherein said vibration absorbing material comprises vibration absorbing rubber.
9. The blade holding structure for supersonic planar cascade test of claim 5, wherein said joint surface is bonded to an outer surface outside of the louver flow channel by means of bonding.
10. The blade holding structure for supersonic planar cascade test of claim 9, wherein said bonding is a removable soft gel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310733580.4A CN116519307A (en) | 2023-06-20 | 2023-06-20 | Blade fixing structure for supersonic plane blade grid test and design method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310733580.4A CN116519307A (en) | 2023-06-20 | 2023-06-20 | Blade fixing structure for supersonic plane blade grid test and design method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116519307A true CN116519307A (en) | 2023-08-01 |
Family
ID=87397870
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310733580.4A Pending CN116519307A (en) | 2023-06-20 | 2023-06-20 | Blade fixing structure for supersonic plane blade grid test and design method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116519307A (en) |
-
2023
- 2023-06-20 CN CN202310733580.4A patent/CN116519307A/en active Pending
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