CN114705413A - Blade mounting structure and method fastened by main flow aerodynamic force and application thereof - Google Patents
Blade mounting structure and method fastened by main flow aerodynamic force and application thereof Download PDFInfo
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- CN114705413A CN114705413A CN202210401466.7A CN202210401466A CN114705413A CN 114705413 A CN114705413 A CN 114705413A CN 202210401466 A CN202210401466 A CN 202210401466A CN 114705413 A CN114705413 A CN 114705413A
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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
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- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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Abstract
The invention discloses a blade mounting structure fastened by using main flow aerodynamic force, a method and application thereof, and relates to the technical field of blade grid test blade mounting. The key points of the technical scheme are as follows: the test bench is equipped with the mount pad, and is rotatory after inserting the wall with the blade base, utilizes mainstream to make the blade fixed to the aerodynamic force of blade, need not other parts and instrument, and the installation is simple, can shorten blade installation time.
Description
Technical Field
The invention belongs to the technical field of blade grid test blade installation, and particularly relates to a blade installation structure fastened by using main flow aerodynamic force, an installation method and application thereof.
Background
A gas turbine engine is a thermodynamic device based on the brayton cycle, which has been widely used in modern military and industry by virtue of its powerful output power and high thermal efficiency. The indispensable compressor part and turbine part in the engine are both impellers, and blades are needed for decelerating, expanding or contracting a channel, accelerating airflow, reducing temperature or doing work; in the blade-related test, whether the static blade cascade test is directed to a static blade (or a guide blade) or a movable blade, the static blade cascade test is an important test form for designing and verifying the blade-related performance. In the test, the blade is required to be installed and fixed in the blade grid channel under the mainstream conditions.
At present, the fixing mode of the static cascade test blade is generally flange bolt connection or tenon connection. The flange bolt connection mode needs a large number of bolt structures, so that the process of replacing the test piece is time-consuming and labor-consuming, certain static cascade tests are carried out in the cavity, and the compact test bed cavity cannot provide necessary space for the wrench to stretch into in the disassembling and assembling processes of the bolts. While the types of tenons for the dovetail connection include pin tenons, axial dovetails, annular dovetails, fir-tree tenons. During operation, aerodynamic forces may cause the blade to move in the direction of the slot, and therefore the dovetail connection requires a locking arrangement. The locking structure increases the number of parts, and the locking structure often utilizes the plastic deformation of the structure of the locking structure to provide the force required by installation and fixation, and is not desirable in a static blade cascade test which needs to repeatedly replace the blade. In the cascade test, the time for replacing the blade is usually higher in specific gravity in the whole test period, and the fixing effect of the blade directly determines the safety degree in the test process and the reliability of the test result.
In addition, the prior art is, for example, the chinese patent application, the application number thereof: CN2019104427051, publication No.: CN110145372A discloses a turbine rotor forked blade mounting structure, relates to turbine blade installation technical field, when aiming at solving traditional installation blade, can't eliminate the problem in installation clearance, and its technical scheme main points are: the blade locking mechanism comprises a rotor and fork-shaped blades connected to the rotor, wherein the side wall of the rotor is connected with a mounting seat, an annular fork-shaped wheel groove is coaxially formed in the mounting seat and the rotor, a plurality of middle blades are slidably clamped in the fork-shaped wheel groove, a wheel groove is radially formed in the side wall of the fork-shaped wheel groove along the rotor, a last blade penetrates through the wheel groove, and a locking assembly used for locking the last blade is arranged in the wheel groove. Application No.: CN2017108308230, publication No.: CN107725117A discloses a stator blade mounting structure that can be applied to fields such as ground gas turbine, aeroengine, including the stator blade of taking the clamp plate, interior outer loop light elastic component, interior outer loop machine casket and the clamp for the outer ring clamp plate. Through the parts, the detachable function of the single blade of the stator blade can be realized, and the assembly and the positioning of the whole-ring stator blade are realized by using the light elastic piece and the cold interference magnitude of the inner and outer ring blade profiles of the blade. In the assembled state, the assembly has certain rigidity and can transmit the aerodynamic torque of the stator blade to the corresponding position of the mounting edge of the casing.
However, the prior art is complicated to install and is not favorable for installation and positioning. Therefore, the blade mounting structure is improved, the number of parts is reduced as far as possible, the mounting steps are simplified, and the space required by mounting is reduced on the premise of ensuring the reliability, so that the blade mounting structure is very necessary and meaningful for improving the test efficiency of the static blade cascade.
Disclosure of Invention
In order to improve the efficiency of a static cascade test and realize the installation of the blades in a limited space, the invention provides a blade installation structure fastened by using main flow aerodynamic force and an installation method thereof, and the blade installation structure has the advantage of simple installation.
The purpose of the invention is realized by the following technical scheme:
the utility model provides an utilize blade mounting structure of mainstream aerodynamic fastening, includes blade, test bench, blade base, mount pad, characterized in that:
blade base and mount pad are contacted each other, play the effect of connecting blade and test bench, guarantee at the test process, the blade can be fixed on the test bench, the blade base is formed by incomplete disk, incomplete rectangle piece, cylinder stack, and the axis of incomplete disk and cylinder axis coincidence, the nodical on incomplete rectangle piece diagonal are on the cylinder axis for can be rotatory around this axis after incomplete rectangle piece inserts the test bench.
The mounting seat is provided with an inlet cavity, a rotating cavity and a positioning cavity. The rotating cavity is formed by penetrating the mounting seat in the shape of the plan view of the incomplete circular disc, so that the axis of the incomplete circular disc is coincident with the axis of the rotating cavity. Get into the chamber and form by the downward groove that link up, circular arc trough of belt and the constant head tank of seting up in the mount pad, the downward groove that link up is the same with incomplete rectangular sheet end shape for incomplete rectangular sheet can insert to the circular arc trough of belt. The positioning cavity is an arc belt groove formed in the mounting seat.
Preferably: the outer diameter of the circular arc belt groove entering the cavity and the positioning cavity is the same as the length of the diagonal line of the incomplete rectangular sheet, and the height of the circular arc belt groove is the same as the thickness of the incomplete rectangular sheet.
Preferably: after the blades are inserted, the incomplete rectangular sheet can rotate in the arc-shaped belt groove and cannot move up and down along the normal direction of the plane of the test bed, so that the fixing in the axial direction is realized.
Preferably: the distance between the upper surface of the circular-arc groove and the lower surface of the cascade channel is the same as the thickness of the incomplete wafer. When the side face of the incomplete rectangular sheet is respectively contacted with the side face of the positioning groove and the side face of the positioning cavity, the blade is just arranged at the mounting position, and at the moment, the incomplete wafer is flush with the incomplete rectangular sheet and the outlet of the test bed.
Preferably: after the blades are installed, the upper surface of the blade base and a blade cascade channel, namely the lower surface of the inner surface of the test bed, are on the same plane, and the blade cascade channel is flat; the blade base does not protrude out of the test bed at the tail edge side of the blade, and the condition of a test outlet is not influenced.
Preferably: the incomplete disc has a diameter greater than the distance between any two points on the test profile and can completely contain the bottom surface of the blade in plan view.
By adopting the technical scheme, the positions of the air paths and the lines which need to be arranged in the blades can be reserved.
The technical scheme is realized by the following technical scheme:
a method of mounting a blade mounting structure utilizing mainstream aerodynamic fastening, comprising the steps of,
s1, inserting the blade from the lower part of the test bed, wherein in the inserting process, the axis of the incomplete wafer is overlapped with the axis of the rotating cavity, one side of the incomplete rectangular sheet is aligned with the shape of the downward through groove, and the inserting direction is the normal direction of the test bed; and (3) until the upper surface of the incomplete rectangular sheet is contacted with the upper surface of the circular arc belt groove, the side surface of the incomplete wafer is contacted with the side surface of the rotating cavity, and the upper surface of the incomplete wafer is aligned with the lower surface of the cascade channel.
And S2, rotating the blade along the cylindrical axis until the side of the incomplete rectangular sheet is contacted with the side of the positioning groove and the side of the positioning cavity respectively.
After installing the blade through adopting above-mentioned technical scheme, in the experiment in-process that carries out, mainstream gas flows along the blade, by the pneumatic principle of blade, blade pressure surface lateral pressure is greater than suction surface lateral pressure, can be according to the blade shape, through setting up cylinder axis position, make mainstream gas produce the same moment of torsion with the installation direction to the aerodynamic force of blade, make incomplete rectangle piece side and constant head tank side, location chamber side sustained contact, it is rotatory to make the unable contrary installation direction of blade base, drop from getting into the chamber, thereby realize the fastening. Meanwhile, the incomplete rectangular sheet is contacted with the side face of the positioning groove, and the incomplete wafer is contacted with the side wall of the rotating cavity, so that the blade cannot fall from the test bed backwards along the main flow direction.
The technical scheme is realized by the following settings: the inlet cavity is arranged at the side of a blade basin after the blade is installed, and the positioning cavity is arranged at the side of a blade back after the blade is installed.
The invention also discloses a method for fixing the static cascade test blade in the gas turbine engine by applying the blade mounting structure fastened by using the main flow aerodynamic force.
The invention also discloses a method for mounting and fixing the blade mounting structure fastened by using main flow aerodynamic force, which is applied to the mounting and fixing process of the static cascade test blade in the gas turbine engine.
Has the beneficial effects that:
when the blade inserts the test bench, the incomplete rectangle piece of blade base is inserted to the circular arc trough of belt through lining up the groove downwards, utilizes incomplete disk and rotatory chamber axis coincidence, and radial positioning is realized in the wall contact, and the blade is the integral rotation back, utilizes circular arc trough of belt thickness and the same axial positioning of realization of incomplete rectangle piece thickness and fixed, utilizes incomplete rectangle piece and constant head tank side, location chamber side to contact and realizes circumferential direction location. After the blades are installed, the blades are fixed by utilizing the aerodynamic force of the main flow, other parts and tools are not needed in the installation process, and the installation time is short.
Drawings
FIG. 1 is an isometric view of a test stand after the blade of the present invention has been installed.
FIG. 2 is an isometric view of a test stand according to the present invention.
Fig. 3 is an isometric view of a blade of the present invention.
FIG. 4 is a rear view of the test stand after the blade of the present invention has been installed.
FIG. 5 is a cross-sectional view D-D of the test rig of the present invention (without the blade) of FIG. 4.
In the figure:
1. a blade; 2. a test bed; 3. a blade base; 4. a mounting seat; 5. an incomplete disc; 6. an incomplete rectangular sheet; 7. a cylinder; 8. entering the cavity; 9. a rotating chamber; 10. a positioning cavity; 11. a downward through groove; 12. positioning a groove; 13. leaf basin side; 14 leaf dorsal side
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
example one
With reference to fig. 1-5, the present embodiment provides a blade mounting structure fastened by using main flow aerodynamic force and a mounting method thereof, and the mounting structure mainly includes a blade 1, a test bed 2, a blade base 3, and a mounting seat 4.
As shown in fig. 1 and 4, the blade mount 3 and the mounting seat 4 contact each other to function as a connection between the blade 1 and the test bed 2.
As shown in fig. 3, the blade base 3 is formed by stacking an incomplete circular sheet 5, an incomplete rectangular sheet 6, and a cylinder 7, wherein the axis of the incomplete circular sheet 5 coincides with the axis of the cylinder 7, and the intersection point of the diagonals of the incomplete rectangular sheet 6 is on the axis of the cylinder 7. In the example, the incomplete round piece 5 had a thickness of 5mm, and the incomplete rectangular piece 6 had a thickness of 10 mm.
As shown in fig. 2 and 4, the mounting seat 4 is provided with an access cavity 8, a rotation cavity 9 and a positioning cavity 10. The rotating cavity 9 is formed by penetrating the incomplete circular sheet 5 in a top view shape, and in combination with the characteristics of the blade base 3 shown in fig. 3, the axes of the incomplete circular sheet 5, the cylinder 7 and the rotating cavity 9 are overlapped, so that the blade 1 and the blade base 3 can rotate around the axis after being inserted into the test bed 2. The inlet chamber 8 is arranged on the basin side 13 of the blade 1 after installation, the positioning chamber 10 is arranged on the back side 14 of the blade 1 after installation, in the example, the inlet chamber 8 is arranged on the left side of a back view, and the positioning chamber 10 is arranged on the right side of the back view, so that the main aerodynamic force can generate the same torque on the blade as the installation direction.
As shown in fig. 5, the entry cavity 8 is formed by a downward through groove 11, an arc groove and a positioning groove 12 in the mounting seat 4, and the downward through groove 11 is the same as the tail end of the incomplete rectangular sheet 6, so that the incomplete rectangular sheet 6 can be inserted into the arc groove. The positioning cavity 10 is provided with an arc-shaped belt groove in the mounting seat.
The distance between the upper surface of the circular arc groove of the inlet cavity 8 and the positioning cavity 10 and the lower bottom surface of the blade grid channel is 5mm, and is the same as the thickness of the incomplete wafer 5, so that after the blade 1 is installed, the upper surface of the blade base 3 can just fill the bottom surface of the blade grid channel, the blade grid channel is flat, and the installation structure cannot influence a test flow field. The external diameter of two circular arc trough of belt equals incomplete rectangular sheet 6 diagonal length, and the circular arc trough of belt height is 10mm, and is the same with incomplete rectangular sheet 6 thickness. After the blade inserts, incomplete rectangle piece 6 can rotate in the circular arc trough of belt, and can't reciprocate along the axial, realizes axial direction's fixed.
When the incomplete rectangular sheet 6 contacts with the side face of the positioning groove 12 and the side face of the positioning cavity 10, the blade is just arranged at the mounting position, the incomplete round sheet 5 and the incomplete rectangular sheet 6 are flush with the outlet of the test bed 2, and the mounting structure does not influence the condition of the test outlet.
The incomplete wafer 5 can completely contain the bottom surface of the blade 1, and positions required by gas circuits and lines arranged in the blade can be reserved.
Example two
A method for mounting a blade mounting structure fastened by means of mainstream aerodynamic forces, comprising the steps of,
s1, insert blade 1 from test bench 2 below, in the insertion process, the direction of insertion is the normal direction of bottom surface under the cascade, in this example, blade 2 trailing edge is left the place ahead towards, make incomplete rectangular sheet 6 in the shape of blade 2 trailing edge side and the alignment of 11 shapes of slot that link up downwards, therefore, incomplete rectangular sheet 6 can be inserted to the circular arc trough of belt through the slot that link up downwards 11, incomplete rectangular sheet upper surface and circular arc trough upper surface contact this moment, incomplete disc upper surface and cascade passageway lower surface parallel and level, incomplete disc side and rotary cavity side face contact, the axis and the rotary cavity 9 axis coincidence of incomplete disc 5 simultaneously, by the above-mentioned radial fixation that realizes.
S2, in this example, the blade 1 and the blade base 3 are rotated counterclockwise in the top view along the axis of the cylinder 7, and when the rotation angle is 90 degrees, the side of the incomplete rectangular piece 6 contacts with the side of the positioning groove 12 and the side of the positioning cavity 10, respectively. In the rotating process, the axial positioning of the blade can be realized by utilizing the thickness of the circular arc belt groove to be the same as that of the incomplete rectangular sheet 6.
Through adopting above-mentioned technical scheme, after installing blade 2, in the experiment in-process that carries out, the aerodynamic force of mainstream gas to blade 1 gives blade 1 and the same moment of torsion of installation direction, be the top view anticlockwise in the example for incomplete rectangle piece 6 and constant head tank 12 side, location chamber 10 side sustained contact make the unable contrary installation direction rotation of blade base 3, drop from getting into chamber 8, realize the circumference location, the position of blade is fixed completely from this, realizes the fastening. The incomplete rectangular sheet 6 is in contact with the side face of the positioning groove 12, and the incomplete circular sheet 5 is in contact with the side wall of the rotating cavity 6, so that the blade 1 cannot fall off from the test bed 2 backwards along the main flow direction.
The embodiments of the present invention are preferred embodiments of the present invention, and the scope of the present invention is not limited by these embodiments, so: equivalent changes made according to the structure, shape and principle of the invention shall be covered by the protection scope of the invention.
Claims (8)
1. The utility model provides an utilize blade mounting structure of mainstream aerodynamic fastening, includes blade (1), test bench (2), blade base (3), mount pad (4), its characterized in that: blade base (3) are in blade (1) below, and mount pad (4) set up in test bench (2), blade base (3) form including incomplete disc (5), incomplete rectangle piece (6), cylinder (7) stack, and the axis of incomplete disc (5) and cylinder (7) axis coincidence, the nodical point of incomplete rectangle piece (6) diagonal are on cylinder (7) axis, and incomplete disc (5) diameter is greater than the distance of arbitrary two points on the experimental leaf type.
2. A blade mounting structure secured by mainstream aerodynamic forces as claimed in claim 1, wherein: the mounting seat (4) is provided with an inlet cavity (8), a rotating cavity (9) and a positioning cavity (10); the inlet cavity (8) is formed by arranging an arc-shaped belt groove, a downward through groove (11) and a positioning groove (12) in the mounting seat (4), and the shape of the downward through groove (11) is the same as that of the tail end of the incomplete rectangular sheet (6); the rotating cavity (9) is formed by stretching the shape of the incomplete wafer (5) in a top view along the normal direction; the positioning cavity (10) is an arc-shaped belt groove formed in the mounting seat (4); the outer diameter of the circular arc belt groove of the entering cavity (8) and the positioning cavity (10) is the length of the diagonal line of the incomplete rectangular sheet (6), and the thickness of the circular arc belt groove is the same as that of the incomplete rectangular sheet (6).
3. A blade mounting structure secured with mainstream aerodynamic forces as defined in claim 2, wherein: the inlet cavity (8) is arranged on the blade basin side (13) after the blade (1) is installed, and the positioning cavity (10) is arranged on the blade back side (14) after the blade (1) is installed.
4. The blade mounting structure fastened by mainstream aerodynamic force according to claim 1, wherein after the mounting is completed, the incomplete round sheet (5) and the incomplete rectangular sheet (6) are mounted and flush with the outlet of the test bed (2); the thickness of the incomplete wafer (5) is the same as the distance from the upper surface of the circular-arc groove to the lower surface of the blade grid channel.
5. A method for installing and fixing a blade installation structure fastened by using main flow aerodynamic force is characterized in that: comprises the following steps
S1, inserting the blade (1) from the lower part of the test bed (2), wherein in the inserting process, the axis of the incomplete wafer (5) is overlapped with the axis of the rotating cavity (9), and the incomplete rectangular sheet (6) is aligned with the downward through groove (11); until the upper surface of the incomplete rectangular sheet (6) is contacted with the upper surface of the circular arc groove, the upper surface of the incomplete wafer (5) is aligned with the lower surface of the cascade channel, and the side surface of the incomplete wafer (5) is contacted with the side surface of the rotary cavity (9);
and S2, rotating the blade (1) along the cylindrical axis until the incomplete rectangular sheet (6) contacts with the side surface of the positioning groove (12) and the side surface of the positioning cavity (10), and placing the blade at the right mounting position.
6. A method of installation and securement of a blade mounting structure utilizing mainstream aerodynamic fastening as claimed in claim 5, wherein: after the steps are carried out, in the test process, the aerodynamic force of the main flow gas on the blade (1) gives the same torque to the blade (1) in the mounting direction, so that the incomplete rectangular sheet (6) is continuously contacted with the side surface of the positioning groove (12) and the side surface of the positioning cavity (10), the blade base (3) cannot rotate in the reverse mounting direction and falls from the inlet cavity (8), and the fixation is realized; meanwhile, the incomplete wafer (5) is in contact with the side wall of the rotating cavity (9), and the incomplete rectangular sheet (6) is in contact with the side face of the positioning groove (12), so that the blade (1) cannot fall off from the test bed (2) along the main flow direction.
7. The use of a blade mounting structure as claimed in any of claims 1 to 4 for fastening with mainstream aerodynamic forces for the fastening of stationary cascade test blades in gas turbine engines.
8. The method for mounting and fixing a blade mounting structure fastened by means of mainstream aerodynamic force as recited in any one of claims 5 to 6 is applied to the mounting and fixing process of a stationary cascade test blade in a gas turbine engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210401466.7A CN114705413B (en) | 2022-04-15 | 2022-04-15 | Blade mounting structure and method fastened by using main flow aerodynamic force and application thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210401466.7A CN114705413B (en) | 2022-04-15 | 2022-04-15 | Blade mounting structure and method fastened by using main flow aerodynamic force and application thereof |
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| CN114705413A true CN114705413A (en) | 2022-07-05 |
| CN114705413B CN114705413B (en) | 2022-12-27 |
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