CN108050101A - A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud - Google Patents
A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud Download PDFInfo
- Publication number
- CN108050101A CN108050101A CN201711374256.9A CN201711374256A CN108050101A CN 108050101 A CN108050101 A CN 108050101A CN 201711374256 A CN201711374256 A CN 201711374256A CN 108050101 A CN108050101 A CN 108050101A
- Authority
- CN
- China
- Prior art keywords
- blade
- outer shroud
- high pressure
- pressure ratio
- easy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000011248 coating agent Substances 0.000 claims abstract description 13
- 238000000576 coating method Methods 0.000 claims abstract description 13
- KMWBBMXGHHLDKL-UHFFFAOYSA-N [AlH3].[Si] Chemical compound [AlH3].[Si] KMWBBMXGHHLDKL-UHFFFAOYSA-N 0.000 claims abstract description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
- F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to gas-turbine plant technical fields, and in particular to a kind of Vessel personnel high pressure ratio compressor blade connects outer shroud, and blade connection outer shroud includes blade, latch and outer shroud；Outer shroud is connected by latch with blade；Outer ring inner surface is equipped with wear-resistant coating；Wear-resistant coating is polybenzoate aluminium silicon coating；The outer radius of blade is equipped with tenon, the axial front and rear boss for respectively having protrusion at one in place, which forms the circular bosses with inside/outside diameter size by whole circle blade, it is circumferentially distributed at the whole circle boss there are six stop hole；Outer shroud is ring, is respectively there is groove at one axially back and forth, and for being coordinated with blade, in the distribution of groove inner circumferential, there are six circular holes.Blade has integral shroud tenon, can individually be mounted and dismounted, and has easy to use, easy to operate and maintain.The present invention's is easy to use, and easy to operate, adaptability is wide, is easy to promotion and application on a large scale.
Description
Technical field：
The invention belongs to gas-turbine plant technical fields, and in particular to a kind of Vessel personnel high pressure ratio compressor blade connects
Connect outer shroud.
Background technology：
Compressor is one of important composition component of Vessel personnel, its function is the machinery that consumption is provided by turbine part
Work(carrys out compressed air, improves the stagnation pressure of air, and the compression of enough pressure and flow is continuously conveyed to combustion chamber components
Air.It is using the air continuously flowed as medium, using blade as main operation element, realize kinetic energy from mechanical energy to fluid,
Potential energy, and with a kind of impeller rotation-type machinery that thermal energy improves.Important component of the compressor as gas turbine
One of, its performance quality can directly affect the overall performance of gas turbine.Compressor blade connection structure（Outer shroud）Always
One of key technology in gas turbine design.Advanced blade connection structure is played for improving compressor installation and maintenance efficiency
Vital effect.In many newly-designed compressors, advanced blade interconnection technique is all employed in varying degrees.Mesh
Before, warship marine gas turbine is generally used for that pressure ratio is relatively low, and outer casing is in point half shape mostly using dove-tail form outer shroud connection structure
State.When compressor pressure ratio is higher（More than 40）When, casing, which cannot use, under normal circumstances divides half structure, while this structure causes
Equipment operation and maintenance is greatly inconvenient.
The content of the invention：
The present invention is to use a kind of new structure to solve domestic Vessel personnel compressor blade connection, it possesses and makes
With the advantages of convenient, easy to operate, adaptability is wide, application easy to promote large-scale.
The technical solution adopted by the present invention is：A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud, the leaf
Piece connection outer shroud includes blade, latch and outer shroud；The outer shroud is connected by latch with blade.
Further, the outer ring inner surface is equipped with wear-resistant coating.
Further, the wear-resistant coating is polybenzoate aluminium silicon coating.
Further, the outer radius of the blade is equipped with tenon, and axial place is front and rear respectively boss raised at one, the boss
Circular bosses with inside/outside diameter size are formed by whole circle blade, circumferentially distributed at whole circle boss there are six stop holes.
Further, the outer shroud is ring, is respectively there is groove at one axially back and forth, for being coordinated with blade,
There are six circular holes for the distribution of groove inner circumferential.
Beneficial effects of the present invention：Easy to use, easy to operate, adaptability is wide, is easy to promotion and application on a large scale.Its
Major advantage is as follows：
（1）, blade have integral shroud tenon, can individually be mounted and dismounted, have it is easy to use, easy to operate and maintain, be easy to
The characteristics of large-scale promotion application；
（2）, outer shroud respectively having groove at one axially back and forth, it is circumferentially distributed to have 6 in groove for being coordinated with blade
Circular hole, while there is wear-resistant coating in outer ring inner surface；
（3）, latch be connected for blade with outer shroud, carry out circumferential stop.Blade is avoided to be circumferentially rotated with outer shroud；
（4）It can be applied to Vessel personnel compressor blade to be connected with outer shroud, can also be applied to aero-engine；Also may be used simultaneously
Applied to particular/special requirement（Such as offshore platform combustion engine）Gas turbine field, application field mainly include military affairs, the energy,
Electric power, traffic, environmental protection etc..
Description of the drawings：
Fig. 1 the structural representation of present invention；
Fig. 2 is the structure diagram of blade in the present invention；
Fig. 3 is the A of Fig. 2 to structure diagram；
Fig. 4 is the structure diagram of outer shroud in the present invention.
Specific embodiment：
With reference to each figure, a kind of Vessel personnel high pressure ratio compressor blade connects outer shroud, and blade connection outer shroud includes blade
1st, latch 2 and outer shroud 3；The outer shroud 3 is connected by latch 2 with blade 1, carries out circumferential braking；3 inner surface of outer shroud
Equipped with wear-resistant coating 4；The wear-resistant coating 4 is polybenzoate aluminium silicon coating；The outer radius of the blade 1 is equipped with tenon, it is axial at
The front and rear boss for respectively having protrusion at one, which forms the circular bosses with certain inside/outside diameter size by whole circle blade, whole
It is circumferentially distributed at circle boss that there are six stop holes；The outer shroud 3 is ring, is respectively there is groove at one axially back and forth, is used for and leaf
Piece 1 is coordinated, and in the distribution of groove inner circumferential, there are six circular holes.The blade 1 have integral shroud tenon, can individually carry out installation and
Dismounting, has the characteristics that application easy to use, easy to operate and maintain, easy to promote large-scale.
Claims (5)
1. a kind of Vessel personnel high pressure ratio compressor blade connects outer shroud, it is characterised in that：Blade connection outer shroud includes
Blade（1）, latch（2）And outer shroud（3）；The outer shroud（3）Pass through latch（2）With blade（1）Connection.
2. a kind of new Vessel personnel high pressure ratio compressor blade connection outer shroud according to claim 1, feature exist
In：The outer shroud（3）Inner surface is equipped with wear-resistant coating（4）.
3. a kind of new Vessel personnel high pressure ratio compressor blade connection outer shroud according to claim 2, feature exist
In：The wear-resistant coating（4）For polybenzoate aluminium silicon coating.
4. a kind of new Vessel personnel high pressure ratio compressor blade connection described in any one of claim 1 to 3 is outer
Ring, it is characterised in that：The blade（1）Outer radius be equipped with tenon, axial place is front and rear respectively boss raised at one, the boss
Circular bosses with inside/outside diameter size are formed by whole circle blade, circumferentially distributed at whole circle boss there are six stop holes.
5. a kind of new Vessel personnel high pressure ratio compressor blade connection described in any one of claim 1 to 3 is outer
Ring, it is characterised in that：The outer shroud（3）For ring, respectively there is groove at one axially back and forth, be used for and blade（1）Coordinated,
In the distribution of groove inner circumferential, there are six circular holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711374256.9A CN108050101A (en) | 2017-12-19 | 2017-12-19 | A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711374256.9A CN108050101A (en) | 2017-12-19 | 2017-12-19 | A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108050101A true CN108050101A (en) | 2018-05-18 |
Family
ID=62129997
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711374256.9A Pending CN108050101A (en) | 2017-12-19 | 2017-12-19 | A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108050101A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110836199A (en) * | 2019-12-12 | 2020-02-25 | 中国船舶重工集团公司第七0三研究所 | A high-pressure-ratio compressed air moving blade and a wheel disc connection structure |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2006884A (en) * | 1977-10-04 | 1979-05-10 | Rolls Royce | Bladed Rotor Assembly for Gas Turbine Engine |
| US4339229A (en) * | 1979-04-14 | 1982-07-13 | Motoren-Und Turbinen-Union Munchen Gmbh | Rotor wheel for axial-flow turbomachinery |
| US4840536A (en) * | 1987-04-07 | 1989-06-20 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Axial guide blade assembly for a compressor stator |
| CN1646791A (en) * | 2003-05-07 | 2005-07-27 | 斯奈克玛马达公司 | Mechanic stator and its mounting/dismounting method |
| CN101008328A (en) * | 2006-01-27 | 2007-08-01 | 三菱重工业株式会社 | Stationary blade ring of axial compressor |
| CN101769172A (en) * | 2008-12-31 | 2010-07-07 | 通用电气公司 | Dovetail rotor blade assembly |
| CN102906375A (en) * | 2010-05-14 | 2013-01-30 | 西门子公司 | Fixing device for a blade of an axial turbine and method of manufacturing the same |
| CN203499730U (en) * | 2013-07-19 | 2014-03-26 | 中国航空工业集团公司沈阳发动机设计研究所 | Multifunctional upper edge plate of turbine guide blade |
| CN104632830A (en) * | 2013-11-08 | 2015-05-20 | 三菱日立电力系统株式会社 | Tapered thread and gas turbine |
| CN105927585A (en) * | 2016-06-02 | 2016-09-07 | 东方电气集团东方汽轮机有限公司 | Axial positioning structure for compressor blade in impeller groove |
| CN106460193A (en) * | 2014-05-27 | 2017-02-22 | 通用电气公司 | Lanthanum molybdat abradable coatings, their methods of formation and use |
| CN207554419U (en) * | 2017-12-19 | 2018-06-29 | 哈尔滨广瀚燃气轮机有限公司 | A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud |
-
2017
- 2017-12-19 CN CN201711374256.9A patent/CN108050101A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2006884A (en) * | 1977-10-04 | 1979-05-10 | Rolls Royce | Bladed Rotor Assembly for Gas Turbine Engine |
| US4339229A (en) * | 1979-04-14 | 1982-07-13 | Motoren-Und Turbinen-Union Munchen Gmbh | Rotor wheel for axial-flow turbomachinery |
| US4840536A (en) * | 1987-04-07 | 1989-06-20 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Axial guide blade assembly for a compressor stator |
| CN1646791A (en) * | 2003-05-07 | 2005-07-27 | 斯奈克玛马达公司 | Mechanic stator and its mounting/dismounting method |
| US20050232759A1 (en) * | 2003-05-07 | 2005-10-20 | Snecma Moteurs | Machine stator and mounting and dismounting methods |
| CN101008328A (en) * | 2006-01-27 | 2007-08-01 | 三菱重工业株式会社 | Stationary blade ring of axial compressor |
| CN101769172A (en) * | 2008-12-31 | 2010-07-07 | 通用电气公司 | Dovetail rotor blade assembly |
| CN102906375A (en) * | 2010-05-14 | 2013-01-30 | 西门子公司 | Fixing device for a blade of an axial turbine and method of manufacturing the same |
| CN203499730U (en) * | 2013-07-19 | 2014-03-26 | 中国航空工业集团公司沈阳发动机设计研究所 | Multifunctional upper edge plate of turbine guide blade |
| CN104632830A (en) * | 2013-11-08 | 2015-05-20 | 三菱日立电力系统株式会社 | Tapered thread and gas turbine |
| CN106460193A (en) * | 2014-05-27 | 2017-02-22 | 通用电气公司 | Lanthanum molybdat abradable coatings, their methods of formation and use |
| CN105927585A (en) * | 2016-06-02 | 2016-09-07 | 东方电气集团东方汽轮机有限公司 | Axial positioning structure for compressor blade in impeller groove |
| CN207554419U (en) * | 2017-12-19 | 2018-06-29 | 哈尔滨广瀚燃气轮机有限公司 | A kind of Vessel personnel high pressure ratio compressor blade connects outer shroud |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110836199A (en) * | 2019-12-12 | 2020-02-25 | 中国船舶重工集团公司第七0三研究所 | A high-pressure-ratio compressed air moving blade and a wheel disc connection structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180518 |
|
| RJ01 | Rejection of invention patent application after publication |