CN114705413B - Blade mounting structure and method fastened by using main flow aerodynamic force and application thereof - Google Patents
Blade mounting structure and method fastened by using main flow aerodynamic force and application thereof Download PDFInfo
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- CN114705413B CN114705413B CN202210401466.7A CN202210401466A CN114705413B CN 114705413 B CN114705413 B CN 114705413B CN 202210401466 A CN202210401466 A CN 202210401466A CN 114705413 B CN114705413 B CN 114705413B
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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
Abstract
The invention discloses a blade mounting structure fastened by using main 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 tests, the blades are required to be installed and fixed in the blade grid channels 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 thereof to provide the force required by installation and fixation, which is not desirable in the static cascade test that needs to repeatedly replace the blade. In the cascade test, the time for replacing the blades is usually higher in specific gravity in the whole test period, and the fixing effect of the blades 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 ring light elastic component, interior outer ring machine casket and outer clamp for the 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 above 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 much 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 static blade cascade test efficiency.
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 rotary cavity is formed by the incomplete disc in plan view shape through the mount so that the incomplete disc coincides with the rotary cavity axis. 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 following components are used: the circular arc trough of belt external diameter that gets into chamber and location chamber is the same with incomplete rectangle piece diagonal length, and the height of circular arc trough of belt is the same with incomplete rectangle piece thickness.
Preferably, the following components are used: 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 following components are used: the distance between the upper surface of the circular arc groove and the lower surface of the blade grid 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, the following components are used: 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 in 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 following components are used: 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.
Through adopting above-mentioned technical scheme, can reserve the inside position that need arrange gas circuit, circuit of blade.
The above technical solution needs to be implemented by the following technical solutions:
a method for mounting a blade mounting structure fastened by means of mainstream aerodynamic forces, comprising the steps of,
s1, inserting a blade from the lower part of a test bed, wherein in the inserting process, the axis of an incomplete wafer is overlapped with the axis of a rotary cavity, one side of an incomplete rectangular sheet is aligned with the shape of a downward through groove, and the inserting direction is the normal direction of the test bed; until the upper surface of the incomplete rectangular sheet is contacted with the upper surface of the arc belt groove, the side surface of the incomplete circular sheet is contacted with the side surface of the rotary cavity, and the upper surface of the incomplete circular sheet is aligned with the lower surface of the cascade channel.
S2, rotating the blade along the axis of the cylinder until the side face of the incomplete rectangular sheet is contacted with the side face of the positioning groove and the side face 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 in contact with the side face of the positioning groove, and the incomplete circular sheet is in contact with the side wall of the rotary cavity, so that the blade cannot fall off from the test bed backwards along the main flow direction.
The technical scheme is realized by the following steps: 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 through lining up the groove downwards, utilizes incomplete disk and rotatory chamber axis coincidence, and the radial positioning is realized in the wall contact, and the blade is whole rotatory 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, the contact of location chamber side to realize circumferential 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 installation of the present invention is complete.
FIG. 5 is a cross-sectional view D-D of the test stand of the present invention (without the blade) of FIG. 4.
In the figure:
1. a blade; 2. a test stand; 3. a blade base; 4. a mounting base; 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. the leaf basin side; 14 dorsal side of the leaf
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 mount 4 contact each other, and function to connect the blade 1 and the test bed 2.
As shown in fig. 3, the blade base 3 is formed by overlapping an incomplete circular sheet 5, an incomplete rectangular sheet 6 and a cylinder 7, the axis of the incomplete circular sheet 5 is coincident 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 thickness of the incomplete circular piece 5 is 5mm, and the thickness of the incomplete rectangular piece 6 is 10mm.
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 shape of the top view of the incomplete wafer 5, and in combination with the characteristics of the blade base 3 shown in fig. 3, the axes of the incomplete wafer 5, the cylinder 7 and the rotating cavity 9 are all 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 blade back side 14 of the blade 1 after installation, in the example, the inlet chamber 8 is arranged on the left side of the rear view, and the positioning chamber 10 is arranged on the right side of the rear 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 inlet chamber 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 has the same shape as the end of the incomplete rectangular piece 6, so that the incomplete rectangular piece 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 of mounting a blade mounting structure utilizing mainstream aerodynamic fastening, 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 cascade bottom surface, in this example, 2 trailing edges of blade are towards left the place ahead, make incomplete rectangular sheet 6 in the shape of 2 trailing edges of blade side and the groove 11 shape of lining up downwards align, therefore, incomplete rectangular sheet 6 can insert to the circular arc trough of belt through lining up groove 11 downwards, incomplete rectangular sheet upper surface and circular arc trough upper surface contact this moment, incomplete disk upper surface and cascade passageway lower surface parallel and level, incomplete disk side and rotation cavity side face contact, the axis of incomplete disk 5 coincides with rotation cavity 9 axis simultaneously, realize radially fixed by the aforesaid.
S2, in the example, the blade 1 and the blade base 3 are integrally rotated along the axis of the cylinder 7 in the anticlockwise direction of the top view, and when the rotation angle is 90 degrees, the side surfaces of the incomplete rectangular sheet 6 are respectively contacted with the side surfaces of the positioning groove 12 and the positioning cavity 10. 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, at 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 counter-clockwise in the example for incomplete rectangle piece 6 and constant head tank 12 side, location chamber 10 side sustained contact, it is rotatory to make the unable contrary installation direction of blade base 3, drop from getting into chamber 8, realize the circumference location, the position of blade is fixed completely from this, realize the fastening. The incomplete rectangular sheet 6 is contacted with the side face of the positioning groove 12, and the incomplete circular sheet 5 is contacted with the side wall of the rotating cavity 6, so that the blade 1 cannot fall from the test bed 2 backwards along the main flow direction.
The embodiments of the present invention are all preferred embodiments of the present invention, and the scope of the present invention is not limited thereby, so: all equivalent changes made according to the structure, shape and principle of the invention are covered by the protection scope of the invention.
Claims (4)
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: the blade base (3) is arranged below the blade (1), the mounting seat (4) is arranged in the test bed (2), the blade base (3) comprises an incomplete wafer (5), an incomplete rectangular sheet (6) and a cylinder (7) which are overlapped, the axis of the incomplete wafer (5) is overlapped with the axis of the cylinder (7), the intersection point of the diagonal lines of the incomplete rectangular sheet (6) is on the axis of the cylinder (7), and the diameter of the incomplete wafer (5) is greater than the distance between any two points on the test blade profile; 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 diameters of the arc belt grooves of the inlet cavity (8) and the positioning cavity (10) are both the length of the diagonal line of the incomplete rectangular sheet (6), and the thickness of the arc belt grooves is the same as that of the incomplete rectangular sheet (6); 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; the entrance cavity (8) is arranged on the left side of the rear view, and the positioning cavity (10) is arranged on the right side of the rear view; this enables the main flow aerodynamic forces to produce the same torque on the blade as the mounting direction.
2. 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.
3. A method of mounting and fixing a blade mounting structure fastened by mainstream aerodynamic force, comprising the blade mounting structure fastened by mainstream aerodynamic force of claim 1, wherein: comprises the following steps
S1, inserting a blade (1) from the lower part of a test bed (2), wherein in the inserting process, the axis of an incomplete wafer (5) is overlapped with the axis of a rotating cavity (9), and an incomplete rectangular sheet (6) is aligned with a 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);
s2, rotating the blade (1) along the axis of the cylinder until the incomplete rectangular sheet (6) is contacted with the side surface of the positioning groove (12) and the side surface of the positioning cavity (10), and placing the blade at the mounting position.
4. A method of installation and securement of a blade mounting structure utilizing mainstream aerodynamic fastening as claimed in claim 3, 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; simultaneously, incomplete disk (5) and rotatory chamber (9) lateral wall contact, incomplete rectangle piece (6) and constant head tank (12) side contact all make blade (1) unable) follow main flow backward from test bench (2) drop.
Priority Applications (1)
| 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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| 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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| CN114705413B true CN114705413B (en) | 2022-12-27 |
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| CN107725117B (en) * | 2017-09-15 | 2019-08-16 | 中国科学院工程热物理研究所 | A kind of stator blade mounting structure |
| CN109931112A (en) * | 2019-04-28 | 2019-06-25 | 杭州汽轮机股份有限公司 | A kind of free blade construction of steam turbine and its assembly method |
| CN110145372B (en) * | 2019-05-25 | 2021-08-10 | 立德动力设备(浙江)有限公司 | Steam turbine rotor forked blade mounting structure and mounting method thereof |
| CN210564669U (en) * | 2019-07-31 | 2020-05-19 | 中国科学院工程热物理研究所 | Blade retainer for impeller machinery |
| FR3107724B1 (en) * | 2020-02-27 | 2022-06-24 | Safran Aircraft Engines | Fan rotor with variable pitch blades and turbomachine equipped with such a rotor |
| CN212296501U (en) * | 2020-03-16 | 2021-01-05 | 西门子工业透平机械（葫芦岛）有限公司 | Blade installation positioning tool and assembly thereof |
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| CN109029889A (en) * | 2018-08-27 | 2018-12-18 | 烟台大学 | A kind of the vibration-testing experimental rig and its test method of blade of aviation engine |
| CN110631933A (en) * | 2019-09-20 | 2019-12-31 | 北京航空航天大学 | High-temperature large-load test fixture and test method for turbine blade joggle joint structure |
| CN110695167A (en) * | 2019-11-08 | 2020-01-17 | 李正玉 | Quick distortion device of fan blade |
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