CN105134303A - Turbine blade edge plate with matched paired rectangular teeth - Google Patents
Turbine blade edge plate with matched paired rectangular teeth Download PDFInfo
- Publication number
- CN105134303A CN105134303A CN201510586578.4A CN201510586578A CN105134303A CN 105134303 A CN105134303 A CN 105134303A CN 201510586578 A CN201510586578 A CN 201510586578A CN 105134303 A CN105134303 A CN 105134303A
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- China
- Prior art keywords
- listrium
- rectangular teeth
- blade
- turbine blade
- edge plate
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine blade edge plate with matched paired rectangular teeth. The turbine blade edge plate comprises blades and edge plate bodies. One edge plate body is installed at the bottom of each blade. Each edge plate body is a rectangle with rectangular teeth on one side. Every two turbine blades are regarded as one group, two edge plate bodies of each group of blades are placed and installed oppositely, the rectangular teeth meshed mutually are arranged on the opposite sides, and the other side of each of the two edge plate is of a plane structure. The plane structures of each group of paired edge plate bodies are matched with those of the adjacent group of edge plate bodies to form planer contact. The turbine blade edge plate with the matched paired rectangular teeth has the advantages that the rigidity and natural vibration frequency of the blades are improved through mutual meshing between the rectangular teeth and the edge plate bodies. By virtue of the planer contact of different groups of edge plate bodies, vibration energy is absorbed through mutual friction during blade vibration, and a vibration reduction role is played.
Description
Technical field
The present invention is directed to the listrium position of turbine blade, belong to mechanical damping vibration damping structure technical field, the turbine blade listrium of particularly a kind of paired rectangular teeth cooperation.
Background technique
Aero engine turbine blades working environment is harsh, not only will bear washing away of High Temperature High Pressure high-speed fuel gas, also will bear the impact force of gas nozzle mechanical periodicity under rotation situation.Turbine rotor blade is because repeatedly occurring in the situation flying accident at home and abroad of the reason such as integral rigidity, intensity, vibration fracture.In order to strengthen turbine blade integral rigidity and resistance to shock, reducing the maximum vibration stress of turbine rotor blade, extending its working life, need to increase damper at the listrium position of turbine blade.
Summary of the invention
The present invention, in order to improve contact damping and the domain blade stiffness of conventional planar listrium, proposes the turbine blade listrium that a kind of convenient installation and the good paired rectangular teeth of effectiveness in vibration suppression coordinate.
The turbine blade listrium that paired rectangular teeth coordinates, each blade bottom installs a listrium; Listrium one side is rectangular teeth, and opposite side-edge is plane structure.
The number of turbine blade is divided into odd and even number two kinds of situations, for the turbine blade of even number number, every two turbine blades is divided into one group, often organizes two listrium installations staggered relatively in blade.
For the turbine blade listrium in one group of blade, opposite side-edge is intermeshing multipair rectangular teeth, and the total number of teeth in engagement of rectangular teeth difference 1;
Be specially: the rectangular teeth of a listrium is positioned at the leaf basin side of place blade, and the rectangular teeth of another listrium is positioned at the blade back side of place blade; Engagement rectangular teeth keeps identical with the thickness of turbine blade listrium.
The facewidth angle value of rectangular teeth produces the area of friction needed for damping and blade integral rigidity is determined, and width calculation is by the length of rectangular teeth place listrium side divided by Integer n, and n chooses according to demand and is generally 3-8;
The tooth depth of rectangular teeth is chosen according to Integer n, and n value is less, and the degree of depth is larger, n value not touch the blade profile line of blade root for limiting value, to ensure area of contact.
The quantity of rectangular teeth is determined by the numerical simulation result of damping vibration attenuation effect or experimental test result.
Every assembly another side to listrium is plane structure, matches with the plane structure of adjacent group listrium, forms plane contact.
For the turbine blade of odd number number, after wherein listrium matches between two, the plane structure with all the other listrium same sizes selected by a remaining listrium, directly and adjacent two paired listrium plane structures match, form plane contact, finally make to be compacted into domain structure between the integral shroud of whole turbine blade.
The invention has the advantages that:
1), the turbine blade listrium that coordinates of a kind of paired rectangular teeth of the present invention, enhance turbine blade integral rigidity and resistance to shock, reduce the maximum vibration stress of turbine rotor blade, extend its working life.
2), the turbine blade listrium that coordinates of a kind of paired rectangular teeth of the present invention, adopt rectangular teeth listrium structure, both easy for installation, make again surface of contact between blade increase.
3), the turbine blade listrium that coordinates of a kind of paired rectangular teeth of the present invention, this structure can provide good damping, also can strengthen blade stiffness better.
Accompanying drawing explanation
Fig. 1 is that the rectangular teeth of the turbine blade listrium that the paired rectangular teeth of the present invention coordinates is at leaf basin direction schematic diagram;
Fig. 2 is the cooperation schematic diagram of the turbine blade listrium that the paired rectangular teeth of the present invention coordinates;
Fig. 3 is turbine blade tip shroud and the listrium schematic diagram of the paired rectangular teeth cooperation of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
The turbine blade listrium that a kind of paired rectangular teeth of the present invention coordinates, the basis of plane contact listrium develops, as depicted in figs. 1 and 2, comprises blade and listrium; The quantity of blade is identical with the quantity of listrium; Each listrium casts in a blade bottom; Listrium one side is rectangular teeth, and opposite side-edge is plane structure; All the other sides can be corrugated, lineal shape, the conventional shapes such as zigzag fashion.
The number of turbine blade is divided into odd and even number two kinds of situations, for the turbine blade of even number number, is one group of paired mounting staggered relatively by every two turbine blades; The opposite side of two turbine blade listriums is intermeshing multipair rectangular teeth, and wherein engaging cross section is rectangular toothing, two turbine blade listrium total number of teeth in engagement differences 1 in a group; The non-Surface of action of another side of two turbine blade listriums is plane structure, organizes turbine blade listrium plane structure directly contact and be close to another.Namely another side of two turbine blade listriums matches with another opposite side organizing the turbine blade listrium of multipair rectangular teeth, forms plane contact.
The position often organizing listrium is specially: the engagement rectangular teeth of a turbine blade listrium is positioned at the leaf basin side of place blade, and the engagement rectangular teeth of another turbine blade listrium is positioned at the blade back side of place blade; The thickness of engagement rectangular teeth and turbine blade listrium remains identical.
The facewidth of engagement rectangular teeth is the forefront that rectangular teeth protrudes, and width produces the area of friction needed for damping and multiple blade integral rigidity is determined, and width calculation is by the length of rectangular teeth place listrium side divided by Integer n, and n chooses according to demand and is generally 3-8;
The engagement tooth depth of rectangular teeth and the wide perpendicular of rectangular teeth, the degree of depth is chosen according to Integer n, and n value is less, and the degree of depth is comparatively large, not touch the blade profile line of blade root for limiting value, to ensure area of contact.The quantity of engaging tooth is determined by the numerical simulation result of damping vibration attenuation effect or experimental test result.
For the turbine blade of odd number number, after wherein listrium matches between two, the plane structure with all the other listrium same sizes selected by a remaining listrium, directly and adjacent two paired listrium plane structures match, form plane contact, finally make to be compacted into domain structure between the listrium of whole turbine blade.
As shown in Figure 3, the scheme that the paired rectangular teeth of the present invention coordinates not only is applied in the integral shroud of turbine blade, can be applied to the listrium of turbine blade equally in an identical manner, or the integral shroud of turbine blade and listrium all adopt rectangular teeth to coordinate; And when the integral shroud of turbine blade and listrium all adopt rectangular teeth to coordinate, rectangular teeth mating part interlaced arrangement also can be made.
The turbine blade listrium that a kind of multipair rectangular teeth of the present invention coordinates, wherein one group of listrium engages each other and can increase blade rigid, improves the natural frequency of vibration of blade; The plane contact of different group listrium, when blade vibration, by triboabsorption vibrational energy each other, can play damping effect.This structure can be applicable in the middle of the engine turbine blade of civil aircraft/military secret all size thrust/power; Blade stiffness and resistance to shock can be improved, extend the working life of blade.
Claims (6)
1. a turbine blade listrium for paired rectangular teeth cooperation, is characterized in that: each blade bottom installs a listrium; Listrium is that a side is designed with rectangular teeth, and opposite side-edge is plane structure;
Every two blades are divided into one group, and the rectangular teeth of two listriums often organized in blade is oppositely arranged, and engages each other, and in two adjacent groups blade, the plane structure of adjacent listrium coordinates contact.
2. the turbine blade listrium of a kind of paired rectangular teeth cooperation as claimed in claim 1, it is characterized in that: when described blade is odd number, a remaining listrium opposite side-edge all adopts plane structure, coordinates respectively contact with the plane structure of listrium in two adjacent groups blade.
3. the turbine blade listrium of a kind of paired rectangular teeth cooperation as claimed in claim 1, it is characterized in that: described listrium is specifically installed as: the rectangular teeth often organizing a listrium in blade is positioned at the leaf basin side of place blade, and the rectangular teeth of another listrium is positioned at the blade back side of place blade; And the number of teeth of the rectangular teeth of two listriums difference 1.
4. the turbine blade listrium that coordinates of a kind of paired rectangular teeth as claimed in claim 1, is characterized in that: the facewidth of described rectangular teeth be the length of rectangular teeth place listrium side divided by Integer n, n is 3 ~ 8.
5. the turbine blade listrium of a kind of paired rectangular teeth cooperation as claimed in claim 1, is characterized in that: the tooth depth of described rectangular teeth need not touch the blade profile line of blade root.
6. the turbine blade listrium of a kind of paired rectangular teeth cooperation as claimed in claim 1, is characterized in that: the thickness of described rectangular teeth is identical with the thickness of listrium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510586578.4A CN105134303B (en) | 2015-09-15 | 2015-09-15 | The turbo blade listrium that a kind of paired rectangular teeth coordinates |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510586578.4A CN105134303B (en) | 2015-09-15 | 2015-09-15 | The turbo blade listrium that a kind of paired rectangular teeth coordinates |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105134303A true CN105134303A (en) | 2015-12-09 |
| CN105134303B CN105134303B (en) | 2017-01-04 |
Family
ID=54719837
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510586578.4A Expired - Fee Related CN105134303B (en) | 2015-09-15 | 2015-09-15 | The turbo blade listrium that a kind of paired rectangular teeth coordinates |
Country Status (1)
| Country | Link |
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| CN (1) | CN105134303B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412826A (en) * | 2020-10-28 | 2022-04-29 | 中国航发商用航空发动机有限责任公司 | Rotor blade, rotor assembly and gas turbine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5242270A (en) * | 1992-01-31 | 1993-09-07 | Westinghouse Electric Corp. | Platform motion restraints for freestanding turbine blades |
| CN101336335A (en) * | 2005-12-01 | 2008-12-31 | 株式会社东芝 | Turbine rotor blade, turbine rotor and steam turbine comprising them |
| CN201339493Y (en) * | 2009-01-06 | 2009-11-04 | 长沙理工大学 | Vibration absorber used for turbine blades |
| US20100014978A1 (en) * | 2006-09-25 | 2010-01-21 | Rene James Webb | Turbine rotor with locking plates and corresponding assembly method |
| JP2012072750A (en) * | 2010-09-30 | 2012-04-12 | Hitachi Ltd | Turbine moving blade |
| EP2598721B1 (en) * | 2010-07-27 | 2014-04-23 | Snecma | Turbine or compressor wheel of a turbomachine |
-
2015
- 2015-09-15 CN CN201510586578.4A patent/CN105134303B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5242270A (en) * | 1992-01-31 | 1993-09-07 | Westinghouse Electric Corp. | Platform motion restraints for freestanding turbine blades |
| CN101336335A (en) * | 2005-12-01 | 2008-12-31 | 株式会社东芝 | Turbine rotor blade, turbine rotor and steam turbine comprising them |
| US20100014978A1 (en) * | 2006-09-25 | 2010-01-21 | Rene James Webb | Turbine rotor with locking plates and corresponding assembly method |
| CN201339493Y (en) * | 2009-01-06 | 2009-11-04 | 长沙理工大学 | Vibration absorber used for turbine blades |
| EP2598721B1 (en) * | 2010-07-27 | 2014-04-23 | Snecma | Turbine or compressor wheel of a turbomachine |
| JP2012072750A (en) * | 2010-09-30 | 2012-04-12 | Hitachi Ltd | Turbine moving blade |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412826A (en) * | 2020-10-28 | 2022-04-29 | 中国航发商用航空发动机有限责任公司 | Rotor blade, rotor assembly and gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105134303B (en) | 2017-01-04 |
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Granted publication date: 20170104 Termination date: 20180915 |