CN105134303B - The turbo blade listrium that a kind of paired rectangular teeth coordinates - Google Patents
The turbo blade listrium that a kind of paired rectangular teeth coordinates Download PDFInfo
- Publication number
- CN105134303B CN105134303B CN201510586578.4A CN201510586578A CN105134303B CN 105134303 B CN105134303 B CN 105134303B CN 201510586578 A CN201510586578 A CN 201510586578A CN 105134303 B CN105134303 B CN 105134303B
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- CN
- China
- Prior art keywords
- listrium
- blade
- rectangular teeth
- coordinates
- turbo blade
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- Expired - Fee Related
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses the turbo blade listrium that a kind of paired rectangular teeth coordinates, including blade and listrium；Each blade bottom installs a listrium；Listrium be side be the rectangle of rectangular teeth.Each two turbo blade being divided into one group, often two listrium installations staggered relatively in group blade, opposite side is intermeshing rectangular teeth, and the opposite side of two listriums is planar structure；Often form the planar structure to listrium to match with the planar structure of adjacent sets listrium, form plane contact.Advantage is, by engaging each other between rectangular teeth listrium, increases blade rigidity, improves the natural frequency of vibration of blade；The plane contact of different group listriums, when blade vibration, by triboabsorption vibrational energy each other, plays damping effect.
Description
Technical field
The present invention is directed to the listrium position of turbo blade, belong to mechanical damping vibration-proof structure technical field, particularly to one
Plant the turbo blade listrium that paired rectangular teeth coordinates.
Background technology
Aero engine turbine blades working environment is harsh, washing away of High Temperature High Pressure high-speed fuel gas to be born, and also wants
The impulsive force of gas nozzle mechanical periodicity is born under rotation situation.Turbine rotor blade is former because of integral rigidity, intensity, vibration etc.
Because the situation aviation accident at home and abroad of fracture repeatedly occurs.In order to strengthen turbo blade integral rigidity and resistance to shock,
Reduce the maximum vibration stress of turbine rotor blade, extend its service life, need to increase at the listrium position of turbo blade resistance
Buddhist nun's device.
Summary of the invention
The present invention in order to improve contact damping and the domain blade stiffness of conventional planar listrium, propose a kind of convenient installation and
The turbo blade listrium of the paired rectangular teeth cooperation that effectiveness in vibration suppression is good.
The turbo blade listrium that a kind of paired rectangular teeth coordinates, each blade bottom installs a listrium；Listrium side
While be rectangular teeth, relative side is planar structure.
The number of turbo blade is divided into two kinds of situations of odd and even number, for the turbo blade of even number number, by each two
Turbo blade is divided into one group, often two listrium installations staggered relatively in group blade.
For the turbo blade listrium in one group of blade, relative side is intermeshing multipair rectangular teeth, and rectangular teeth
Total number of teeth in engagement difference 1；
Particularly as follows: the rectangular teeth of a listrium is positioned at the leaf basin side of place blade, the rectangular teeth of another listrium is positioned at institute
Blade back side at blade；Engagement rectangular teeth keeps identical with the thickness of turbo blade listrium.
Depending on the facewidth angle value of rectangular teeth is by damping the required area producing friction and blade integral rigidity, width calculation by
The length of rectangular teeth place listrium side is divided by Integer n, and n chooses usually 3-8 as desired；
The tooth depth of rectangular teeth is chosen according to Integer n, and n value is the least, and the degree of depth is the biggest, and n value is not to touch outside the blade of blade root
Shape line is ultimate value, to ensure contact area.
The quantity of rectangular teeth is determined by numerical simulation result or the experimental test result of damping vibration attenuation effect.
Often assembling another side to listrium is planar structure, matches with the planar structure of adjacent sets listrium, is formed flat
Face contacts.
For the turbo blade of odd number number, after the pairing of listrium the most two-by-two, a remaining listrium is selected and remaining
The planar structure of listrium same size, directly matches with adjacent two paired listrium planar structures, forms plane contact,
Make to be compacted between the integral shroud of whole turbo blade domain structure eventually.
It is an advantage of the current invention that:
1), the turbo blade listrium that coordinates of a kind of paired rectangular teeth of the present invention, enhance turbo blade integral rigidity and anti-
Shake performance, reduce the maximum vibration stress of turbine rotor blade, extend its service life.
2), a kind of paired rectangular teeth of the present invention coordinate turbo blade listrium, use rectangular teeth listrium structure, both sides of installation
Just, contact surface between blade is made again to increase.
3), a kind of paired rectangular teeth of the present invention coordinate turbo blade listrium, this structure can provide good damping to imitate
Really, it is also possible to preferably strengthen blade stiffness.
Accompanying drawing explanation
Fig. 1 is that the rectangular teeth of the turbo 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 turbo 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 present invention paired rectangular teeth cooperation.
In figure:
1. blade；2. listrium；3. rectangular teeth；4. integral shroud；
101. leaf basins；102. blade back；
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
The turbo blade listrium that a kind of paired rectangular teeth of the present invention coordinates, develops on the basis of plane contact listrium
, as depicted in figs. 1 and 2, including blade 1 and listrium 2；The quantity of blade is identical with the quantity of listrium；Each listrium is cast
At a blade bottom；Listrium one side is rectangular teeth 3, and relative side is planar structure；Remaining side can be corrugated, directly
Linear, the conventional shape such as zigzag.
The number of turbo blade is divided into two kinds of situations of odd and even number, for the turbo blade of even number number, by each two
Turbo blade is one group of mounted in pairs staggered relatively；The opposite side of two turbo blade listriums is intermeshing multipair rectangle
Tooth, wherein engagement cross section is rectangular toothing, two turbo blade listrium total number of teeth in engagement differences 1 in a group；Two turbines
The non-field of conjugate action of another side of blade listrium is planar structure, directly contacts with another group turbo blade listrium planar structure and leans on
Tightly.Namely another side of two turbo blade listriums organizes the opposite side phase of turbo blade listrium of multipair rectangular teeth with another
Coordinate, form plane contact.
Often organize the position of listrium particularly as follows: the engagement rectangular teeth of a turbo blade listrium is positioned at the leaf basin of place blade
101 sides, the engagement rectangular teeth of another turbo blade listrium is positioned at blade back 102 side of place blade；Engagement rectangular teeth and turbine
The thickness of blade listrium remains identical.
The facewidth engaging rectangular teeth is the forefront that rectangular teeth protrudes, and width is by damping the required area of friction that produces with many
Depending on individual blade integral rigidity, width calculation is chosen divided by Integer n, n as desired by the length of rectangular teeth place listrium side
Usually 3-8；
The tooth depth of engagement rectangular teeth is perpendicular with the width of rectangular teeth, and the degree of depth is chosen according to Integer n, and n value is the least, and the degree of depth is relatively
Greatly, with do not touch blade root blade profile line as ultimate value, to ensure contact area.The quantity of engaging tooth is imitated by damping vibration attenuation
Numerical simulation result or the experimental test result of fruit determine.
For the turbo blade of odd number number, after the pairing of listrium the most two-by-two, a remaining listrium is selected and remaining
The planar structure of listrium same size, directly matches with adjacent two paired listrium planar structures, forms plane contact,
Make to be compacted between the listrium of whole turbo blade domain structure eventually.
As it is shown on figure 3, the scheme that the paired rectangular teeth of the present invention coordinates is not applied only to the integral shroud 1 of turbo blade, equally may be used
It is applied to the listrium 2 of turbo blade 1 in an identical manner, or the integral shroud 4 of turbo blade and listrium 2 all use rectangular teeth to join
Close；And when the integral shroud of turbo blade and listrium all use rectangular teeth to coordinate, rectangular teeth 4 mating part interlaced arrangement also can be made.
The turbo blade listrium that a kind of multipair rectangular teeth of the present invention coordinates, one of which listrium engages each other can increase leaf
Sheet rigidity, improves the natural frequency of vibration of blade；The plane contact of different group listriums, when blade vibration, can be passed through each other
Triboabsorption vibrational energy, plays damping effect.This structure can be applicable to starting of civil aircraft/military secret all size thrust/power
In the middle of machine turbo blade；Blade stiffness and resistance to shock can be improved, extend the service life of blade.
Claims (6)
1. the turbo blade listrium that a paired rectangular teeth coordinates, it is characterised in that: each blade bottom installs a listrium；
Listrium is that a side is designed with rectangular teeth, and relative side is planar structure；
Each two blade is divided into one group, and often the rectangular teeth of two listriums in group blade is oppositely arranged, and engages each other, adjacent
In two groups of blades, the planar structure of adjacent listrium coordinates contact.
The turbo blade listrium that a kind of paired rectangular teeth the most as claimed in claim 1 coordinates, it is characterised in that: described blade
During for odd number, a remaining listrium relative side all uses planar structure, respectively with listrium flat in two adjacent groups blade
Face respective outer side edges contact.
The turbo blade listrium that a kind of paired rectangular teeth the most as claimed in claim 1 coordinates, it is characterised in that: described listrium
Specifically it is installed as: often in group blade, the rectangular teeth of a listrium is positioned at the leaf basin side of place blade, the rectangular teeth of another listrium
It is positioned at the blade back side of place blade；And the number of teeth difference 1 of the rectangular teeth of two listriums.
The turbo blade listrium that a kind of paired rectangular teeth the most as claimed in claim 1 coordinates, it is characterised in that: described rectangle
The facewidth of tooth be the length of rectangular teeth place listrium side divided by Integer n, n is 3～8.
The turbo blade listrium that a kind of paired rectangular teeth the most as claimed in claim 1 coordinates, it is characterised in that: described rectangle
The tooth depth of tooth need to not touch the blade profile line of blade root.
The turbo blade listrium that a kind of paired rectangular teeth the most as claimed in claim 1 coordinates, it is characterised in that: described rectangle
The thickness of tooth 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 CN105134303A (en) | 2015-12-09 |
| CN105134303B true 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 |
|---|---|
| CN (1) | CN105134303B (en) |
Families Citing this family (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 (4)
| 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 |
| EP2598721B1 (en) * | 2010-07-27 | 2014-04-23 | Snecma | Turbine or compressor wheel of a turbomachine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE602006006452D1 (en) * | 2006-09-25 | 2009-06-04 | Siemens Ag | Turbine rotor with closure plates and corresponding assembly process |
| JP5380412B2 (en) * | 2010-09-30 | 2014-01-08 | 株式会社日立製作所 | Turbine blade |
-
2015
- 2015-09-15 CN CN201510586578.4A patent/CN105134303B/en not_active Expired - Fee Related
Patent Citations (4)
| 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 |
| EP2598721B1 (en) * | 2010-07-27 | 2014-04-23 | Snecma | Turbine or compressor wheel of a turbomachine |
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| Publication number | Publication date |
|---|---|
| CN105134303A (en) | 2015-12-09 |
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Granted publication date: 20170104 Termination date: 20180915 |
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| CF01 | Termination of patent right due to non-payment of annual fee |