US3867060A - Shroud assembly - Google Patents
Shroud assembly Download PDFInfo
- Publication number
- US3867060A US3867060A US401455A US40145573A US3867060A US 3867060 A US3867060 A US 3867060A US 401455 A US401455 A US 401455A US 40145573 A US40145573 A US 40145573A US 3867060 A US3867060 A US 3867060A
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- United States
- Prior art keywords
- shroud
- outer casing
- seal
- radially
- shroud segment
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- Expired - Lifetime
Links
- 125000006850 spacer group Chemical group 0.000 claims description 5
- 230000001419 dependent effect Effects 0.000 claims description 2
- 239000012530 fluid Substances 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 4
- 230000013011 mating Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Definitions
- ABSTRACT In a turbomachine, axial flow leakage of motive fluid between rotor blade tips and the inner circumference of the outer casing is sometimes prevented by utilizing an overlapping (labyrinth) seal and shroud assembly between the blade tips and the outer casing. Removal and assembly of the overlapping shroud seal in an annular, non-split outer casing is greatly facilitated by providing a plurality of shroud segments about the blade tip periphery and a radially outer clearance gap between the shroud segments and the outer casing whereby each shroud segment may be moved radially to unlap the seal and permit axial] removal of the seal without disturbing rotor elements.
- This invention relates in general to turbomachines and more particularly to a shroud assembly for a turbomachine of the type having a non-split annular outer casing.
- the rotor blades are surrounded at their peripheries by a circumferential shroud assembly attached to the outer casing of the turbomachine.
- the rotor blade tip and the shroud assembly are closely adjacent one another to form a seal which prevents axial leakage of the motive fluid between the blade tips and the outer casing.
- One type of seal is the so-called labyrinth seal wherein radially extending blade teeth overlap, in the axial direction, radially depending shroud teeth thereby forming an axial seal.
- the overlapping (labyrinth) seal was used exclusively in conjunction with a horizontally split outer casing comprising upper and lower casing halves including upper and lower shroud segments. Replacement of the upper segment was accomplished by removal of the upper casing half. Removal of the lower shroud segment required removal of the rotor, the entire process being costly and time-consuming. It has also now become desirable to employ an annular or non-split outer casing.
- the present invention describes a construction and method for removing an overlapping (labyrinth) type seal and shroud assembly from an outer casing without disturbing the rotor elements.
- a turbomachine including a rotor axially disposed within a non'split, annular outer casing, said rotor including a plurality of radially extending blades, each blade formed with a tip portion having at least one seal tooth and said outer casing including an annular recess adjacent said blade tip portions, an improved shroud assembly as hereinafter described.
- the shroud assembly includes a plurality of arcuate shroud segments disposed in said outer casing annular recess; each shroud segment including a radially depending shroud tooth which overlaps a respective blade tooth in the axial direction forming a labyrinth seal therewith.
- the annual recess is formed with an annular stop for radially locating said shroud segments relative to said blade tips. Moreover, a clearance gap remains between the radially outward portion of each shroud segment and the radially inward surface of said outer casing annular recess for receiving a spacer plate which bears against each shroud segment. Fastening means are provided for attaching each shroud segment to the outer casing. In assembly and disassembly operations, the spacer plate may be removed from said clearance gap whereby each shroud segment may be moved radially and axially.
- FIG. I is a cross section of a turbomachine (lower half removed) disclosing the details of the present invention.
- FIG. 2 is an enlarged cross section of a turbine blade and shroud assembly showing details according to the present invention.
- a turbomachine portion 11 includes annular outer casings 13 which may be axially joined at circumferential flanges 13a and 13b.
- the annular casings may be nozzle casings, exhaust casings, etc., as is well known in the art.
- the present invention finds its greatest utility in an annular or non-split outer casing, that is, a casing having no horizontal joint for assembly and disassembly. However, it will become apparent that the present invention may be applied to a horizontally split outer casing, if so desired.
- a rotor 15 is axially disposed within the outer casing and may include a high pressure wheel 17 and also a low pressure wheel 19. Each wheel contains radially extending blades 21 circumferentially mounted about the respective rotor wheels, as is well known in the art.
- FIG. 2 in conjunction with FIG. 1, shows a rotor blade 21 mounted within the outer casing 13.
- Each rotor blade includes a tip portion comprising a plurality of seal teeth 23.
- the blade seal teeth are disposed to extend radially. outward from the blade tip.
- the blade teeth form one portion of an axially extending labyrinth seal 25.
- the remaining portion of the labyrinth seal comprises an annular shroud assembly formed by a plurality of shroud segments 27 (only one shown) disposed radially outwardly of the blade seal teeth, and having radially depending shroud teeth 29 overlapping in the axial direction, the blade seal teeth.
- the shroud seal teeth extend radially inwardly between the radially outwardly extending blade teeth to create an interference in the axial direction.
- Each shroud segment is arcuate and the seal teeth may take the form of a number of arcuate rows.
- the shroud segments are disposed in an annular recess 31 formed in the outer casing.
- An annular stop means 33 extends axially into the annular recess.
- the shroud segment is formed with a mating recess 35 which abuts the stop means when. the shroud segment is properly seated into the annular recess.
- the mating recess 35 is elongated to permit radial movement of the shroud segment in the casing annular recess when the mating recess is proximate the stop means.
- Each shroud segment is also formed with an axial bore 41 therethrough whereas the outer casing also includes an aligned bore 43.
- a fastener 45 is threaded through the shroud bore and into the outer casing bore for fastening the shroud segment to the outer casing.
- Each shroud segment includes a radially outward surface 49 which is spaced from a radially inward surface 51 of the outer casing thereby defining an arcuate clearance 53 for allowing radial displacement of the shroud during assembly and disassembly.
- a spacer plate 55 is inserted into the clearance 53 for positioning the shroud segment radially inwardly toward the blade tips.
- each shroud segment may be inserted into a non-split annular turbomachine outer casing to form a labyrinth seal, in the axial direction, with rotor blade seal teeth while the rotor is axially positioned within the outer casing.
- Each shroud segment is axially inserted within the outer casing annular recess 31 until contact is made between the shroud segment and the rear wall of the annular recess defined by a depending portion of the outer casing as shown.
- Each shroud segment is held radially outward in the clearance 53 until the proper circumferential position as heretofore defined is achieved.
- each shroud segment is moved radially inward until annular stop 33 is contacted and the respective blade and shroud teeth are disposed in an axially overlapping position.
- Fasteners 45 are then inserted into bores 41 and 43 in the shroud segment and outer casing respectively.
- This assembly is the reverse of the aforementioned procedure whereby the shroud segment is moved radially outward to unlap the blade and shroud teeth and then axially removed.
- shroud segments may be assembled and removed without disturbing the rotor blades.
- a turbomachine including a rotor axially disposed within a unitary outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having at least one radially extending seal tooth; and, said outer casing being formed with an open end annular recess circumferentially adjacent said rotor blades seal teeth; a shroud assembly comprising:
- each shroud segment may be moved radially outward to unlap respective blade and shroud teeth prior to axial removal from the outer casing;
- each shroud segment for engaging a portion of said annular stop.
- a rotor axially disposed within an annular, non-split outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having radially extending seal teeth, and, said outer casing having an open end annular recess circumferentially adjacent said rotor blade seal teeth; a shroud assembly comprising:
- each shroudsegment including a plurality of radially depending shroud seal teeth which overlap said radially extending blade seal teeth in the axial direction forming an axial labyrinth seal therewith;
- each shroud segment for engaging a portion of said annular stop
- fastening means for attaching each shroud segment to the outer casing.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
In a turbomachine, axial flow leakage of motive fluid between rotor blade tips and the inner circumference of the outer casing is sometimes prevented by utilizing an overlapping (labyrinth) seal and shroud assembly between the blade tips and the outer casing. Removal and assembly of the overlapping shroud seal in an annular, non-split outer casing is greatly facilitated by providing a plurality of shroud segments about the blade tip periphery and a radially outer clearance gap between the shroud segments and the outer casing whereby each shroud segment may be moved radially to unlap the seal and permit axial removal of the seal without disturbing rotor elements.
Description
United States Patent [191 Huber Feb. 18, 1975 SHROUD ASSEMBLY [75] Inventor: Thomas R. Huber, Waterford, N.Y.
[73] Assignee: General Electric Company,
Schenectady, N.Y.
[22] Filed: Sept. 27, 1973 [21] Appl. No.: 401,455
[52] 11.8. C1 415/172 A, 277/54, 415/209 [51] int. Cl. FOld 5/20 [58] Field of Search 4'15/170 R, 171, 172 A, 415/173, 209; 277/54, 56
[56] References Cited UNITED STATES PATENTS 2,416,268 2/1947 Nagler 415/171 2,956,733 10/1960 Stalker 415/170 R FOREIGN PATENTS OR APPLICATIONS 200,055 11/1955 Australia 415/172 A 19,669 0/1908 Great Britain 277/56 444,814 3/1936 Great Britain 277/56 Primary Examinerl-lenry F. Raduazo Attorney, Agent, or Firm-Erwin IF. Berrier, Jr.
[57] ABSTRACT In a turbomachine, axial flow leakage of motive fluid between rotor blade tips and the inner circumference of the outer casing is sometimes prevented by utilizing an overlapping (labyrinth) seal and shroud assembly between the blade tips and the outer casing. Removal and assembly of the overlapping shroud seal in an annular, non-split outer casing is greatly facilitated by providing a plurality of shroud segments about the blade tip periphery and a radially outer clearance gap between the shroud segments and the outer casing whereby each shroud segment may be moved radially to unlap the seal and permit axial] removal of the seal without disturbing rotor elements.
3 Claims, 2 Drawing Figures Simon!) ASSEMBLY BACKGROUND OF THE INVENTION This invention relates in general to turbomachines and more particularly to a shroud assembly for a turbomachine of the type having a non-split annular outer casing.
In a turbomachine, the rotor blades are surrounded at their peripheries by a circumferential shroud assembly attached to the outer casing of the turbomachine. The rotor blade tip and the shroud assembly are closely adjacent one another to form a seal which prevents axial leakage of the motive fluid between the blade tips and the outer casing. One type of seal is the so-called labyrinth seal wherein radially extending blade teeth overlap, in the axial direction, radially depending shroud teeth thereby forming an axial seal.
In the prior art, the overlapping (labyrinth) seal was used exclusively in conjunction with a horizontally split outer casing comprising upper and lower casing halves including upper and lower shroud segments. Replacement of the upper segment was accomplished by removal of the upper casing half. Removal of the lower shroud segment required removal of the rotor, the entire process being costly and time-consuming. It has also now become desirable to employ an annular or non-split outer casing. The present invention describes a construction and method for removing an overlapping (labyrinth) type seal and shroud assembly from an outer casing without disturbing the rotor elements.
It is therefore one object of the present invention to provide an overlapping (labyrinth) seal for an annular, non-split outer casing.
It is another object of the present invention to provide a method for removing a shroud assembly from an annular, non-split casing.
Other objects and advantages will become apparent from the following description of one embodiment of the present invention, and the novel features will be particularly pointed out hereinafter in the claims.
SUMMARY OF THE INVENTION In a turbomachine including a rotor axially disposed within a non'split, annular outer casing, said rotor including a plurality of radially extending blades, each blade formed with a tip portion having at least one seal tooth and said outer casing including an annular recess adjacent said blade tip portions, an improved shroud assembly as hereinafter described. The shroud assembly includes a plurality of arcuate shroud segments disposed in said outer casing annular recess; each shroud segment including a radially depending shroud tooth which overlaps a respective blade tooth in the axial direction forming a labyrinth seal therewith. The annual recess is formed with an annular stop for radially locating said shroud segments relative to said blade tips. Moreover, a clearance gap remains between the radially outward portion of each shroud segment and the radially inward surface of said outer casing annular recess for receiving a spacer plate which bears against each shroud segment. Fastening means are provided for attaching each shroud segment to the outer casing. In assembly and disassembly operations, the spacer plate may be removed from said clearance gap whereby each shroud segment may be moved radially and axially.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. I is a cross section of a turbomachine (lower half removed) disclosing the details of the present invention.
FIG. 2 is an enlarged cross section of a turbine blade and shroud assembly showing details according to the present invention.
DETAILED DESCRIPTION OF THE INVENTION Referring to the drawings, particularly to FIG. 1, a turbomachine portion 11 includes annular outer casings 13 which may be axially joined at circumferential flanges 13a and 13b. The annular casings may be nozzle casings, exhaust casings, etc., as is well known in the art. The present invention finds its greatest utility in an annular or non-split outer casing, that is, a casing having no horizontal joint for assembly and disassembly. However, it will become apparent that the present invention may be applied to a horizontally split outer casing, if so desired.
A rotor 15 is axially disposed within the outer casing and may include a high pressure wheel 17 and also a low pressure wheel 19. Each wheel contains radially extending blades 21 circumferentially mounted about the respective rotor wheels, as is well known in the art.
FIG. 2, in conjunction with FIG. 1, shows a rotor blade 21 mounted within the outer casing 13. Each rotor blade includes a tip portion comprising a plurality of seal teeth 23. The blade seal teeth are disposed to extend radially. outward from the blade tip. The blade teeth form one portion of an axially extending labyrinth seal 25.
The remaining portion of the labyrinth seal comprises an annular shroud assembly formed by a plurality of shroud segments 27 (only one shown) disposed radially outwardly of the blade seal teeth, and having radially depending shroud teeth 29 overlapping in the axial direction, the blade seal teeth. Otherwise stated, the shroud seal teeth extend radially inwardly between the radially outwardly extending blade teeth to create an interference in the axial direction. Each shroud segment is arcuate and the seal teeth may take the form of a number of arcuate rows.
The shroud segments are disposed in an annular recess 31 formed in the outer casing. An annular stop means 33 extends axially into the annular recess. The shroud segment is formed with a mating recess 35 which abuts the stop means when. the shroud segment is properly seated into the annular recess. The mating recess 35 is elongated to permit radial movement of the shroud segment in the casing annular recess when the mating recess is proximate the stop means. Each shroud segment is also formed with an axial bore 41 therethrough whereas the outer casing also includes an aligned bore 43. A fastener 45 is threaded through the shroud bore and into the outer casing bore for fastening the shroud segment to the outer casing.
Each shroud segment includes a radially outward surface 49 which is spaced from a radially inward surface 51 of the outer casing thereby defining an arcuate clearance 53 for allowing radial displacement of the shroud during assembly and disassembly. After assembly of each shroud, a spacer plate 55 is inserted into the clearance 53 for positioning the shroud segment radially inwardly toward the blade tips.
Having described the construction of the present invention, the operation is as follows. With an adjacent casing removed, individual shroud segments may be inserted into a non-split annular turbomachine outer casing to form a labyrinth seal, in the axial direction, with rotor blade seal teeth while the rotor is axially positioned within the outer casing. Each shroud segment is axially inserted within the outer casing annular recess 31 until contact is made between the shroud segment and the rear wall of the annular recess defined by a depending portion of the outer casing as shown. Each shroud segment is held radially outward in the clearance 53 until the proper circumferential position as heretofore defined is achieved. Thereafter, each shroud segment is moved radially inward until annular stop 33 is contacted and the respective blade and shroud teeth are disposed in an axially overlapping position. Fasteners 45 are then inserted into bores 41 and 43 in the shroud segment and outer casing respectively. This assembly is the reverse of the aforementioned procedure whereby the shroud segment is moved radially outward to unlap the blade and shroud teeth and then axially removed. Thus, in an annular non-split outer casing shroud segments may be assembled and removed without disturbing the rotor blades.
While a specific embodiment of the invention has been shown, it will be obvious to those skilled in the art that changes and modifications may be made without departing from the invention. It is therefore intended in the appended claims to cover all such changes and modifications that fall within the true spirit and scope of the invention.
What is claimed is:
1. In a turbomachine, including a rotor axially disposed within a unitary outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having at least one radially extending seal tooth; and, said outer casing being formed with an open end annular recess circumferentially adjacent said rotor blades seal teeth; a shroud assembly comprising:
a plurality of shroud segments disposed in said open end annular recess;
at least one shroud seal tooth radially dependent from each shroud segment and overlapping a blade seal tooth in the axial direction to form an axial seal therewith; and,
a clearance defined between a radially outer surface of each shroud segment and a radially inner surface of said outer casing whereby each shroud segment may be moved radially outward to unlap respective blade and shroud teeth prior to axial removal from the outer casing;
an annular stop formed on said outer casing extending axially into said annular recess; and,
a recess formed in each shroud segment for engaging a portion of said annular stop.
2. The shroud assembly recited in claim 1 wherein said recess formed in the shroud segment is elongated in the radial direction to allow radial positioning of the shroud segment when the shroud segment recess is proximate to the annular stop.
3. In a turbomachine a rotor axially disposed within an annular, non-split outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having radially extending seal teeth, and, said outer casing having an open end annular recess circumferentially adjacent said rotor blade seal teeth; a shroud assembly comprising:
a plurality of shroud segments disposed in said open end annular recess; each shroudsegment including a plurality of radially depending shroud seal teeth which overlap said radially extending blade seal teeth in the axial direction forming an axial labyrinth seal therewith;
a clearance defined between a radially outer surface of each shroud segment and a radially inner surface of said outer casing;
a spacer plate removably positioned in said clearance between each shroud segment and the outer casing;
an annular stop formed on saidouter casing extending axially into said annular recess;
a recess formed in each shroud segment for engaging a portion of said annular stop; and,
fastening means for attaching each shroud segment to the outer casing.
Claims (3)
1. In a turbomachine, including a rotor axially disposed within a unitary outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having at least one radially extending seal tooth; and, said outer casing being formed with an open end annular recess circumferentially adjacent said rotor blades seal teeth; a shroud assembly comprising: a plurality of shroud segments disposed in said open end annular recess; at least one shroud seal tooth radially dependent from each shroud segment and overlapping a blade seal tooth in the axial direction to form an axial seal therewith; and, a clearance defined between a radially outer surface of each shroud segment and a radially inner surface of said outer casing whereby each shroud segment may be moved radially outward to unlap respective blade and shroud teeth prior to axial removal from the outer casing; an annular stop formed on said outer casing extending axially into said annular recess; and, a recess formed in each shroud segment for engaging a portion of said annular stop.
2. The shroud assembly recited in claim 1 wherein said recess formed in the shroud segment is elongated in the radial direction to allow radial positioning of the shroud segment when the shroud segment recess is proximate to the annular stop.
3. In a turbomachine a rotor axially disposed within an annular, non-split outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having radially extending seal teeth, and, said outer casing having an open end annular recess circumferentially adjacent said rotor blade seal teeth; a shroud assembly comprising: a plurality of shroud segments disposed in said open end annular recess; each shroud segment including a plurality of radially depending shroud seal teeth which overlap said radially extending blade seal teeth in the axial direction forming an axial labyrinth seal therewith; a clearance defined between a radially outer surface of each shroud segment and a radially inner surface of said outer casing; a spacer plate removably positioned in said clearance between each shroud segment and the outer casing; an annular stop formed on said outer casing extending axially into said annular recess; a recess formed in each shroud segment for engaging a portion of said annular stop; and, fastening means for attaching each shroud segment to the outer casing.
Priority Applications (7)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US401455A US3867060A (en) | 1973-09-27 | 1973-09-27 | Shroud assembly |
| CA205,865A CA1004143A (en) | 1973-09-27 | 1974-07-29 | Shroud assembly |
| DE2445705A DE2445705C2 (en) | 1973-09-27 | 1974-09-25 | Radial sealing ring |
| FR7432408A FR2245852B1 (en) | 1973-09-27 | 1974-09-26 | |
| JP49110045A JPS5757607B2 (en) | 1973-09-27 | 1974-09-26 | |
| IT27762/74A IT1022359B (en) | 1973-09-27 | 1974-09-26 | SEGMENTED BAND FOR TURBOMACHINE |
| GB4215274A GB1473719A (en) | 1973-09-27 | 1974-09-27 | Turbomachines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US401455A US3867060A (en) | 1973-09-27 | 1973-09-27 | Shroud assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3867060A true US3867060A (en) | 1975-02-18 |
Family
ID=23587839
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US401455A Expired - Lifetime US3867060A (en) | 1973-09-27 | 1973-09-27 | Shroud assembly |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US3867060A (en) |
| JP (1) | JPS5757607B2 (en) |
| CA (1) | CA1004143A (en) |
| DE (1) | DE2445705C2 (en) |
| FR (1) | FR2245852B1 (en) |
| GB (1) | GB1473719A (en) |
| IT (1) | IT1022359B (en) |
Cited By (37)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2470269A1 (en) * | 1979-11-27 | 1981-05-29 | Snecma | RETENTION STRUCTURE FOR A COMPRESSOR CASE OF A TURBOMACHINE |
| FR2483008A1 (en) * | 1980-05-24 | 1981-11-27 | Mtu Muenchen Gmbh | DEVICE FOR MINIMIZING AND MAINTAINING CONSTANT EXTERMITY SETTING OF AXIAL TURBINE BLADES OF GAS TURBINE ENGINES |
| US4697978A (en) * | 1984-07-26 | 1987-10-06 | Matsushita Electric Industrial Co., Ltd. | Industrial robot |
| US4941801A (en) * | 1988-03-23 | 1990-07-17 | Aisin Seiki Kabushiki Kaisha | Double water pump device |
| US5037273A (en) * | 1988-12-19 | 1991-08-06 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Compressor impeller |
| US5362072A (en) * | 1992-12-21 | 1994-11-08 | Imo Industries, Inc., Quabbin Division | Turbine radial adjustable labyrinth seal |
| US5501573A (en) * | 1993-01-29 | 1996-03-26 | Steam Specialties, Inc. | Segmented seal assembly and method for retrofitting the same to turbines and the like |
| US5632598A (en) * | 1995-01-17 | 1997-05-27 | Dresser-Rand | Shrouded axial flow turbo machine utilizing multiple labrinth seals |
| WO2000058607A1 (en) * | 1999-03-31 | 2000-10-05 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie 'nauchno-Proizvodstvennoe Predpriyatie 'motor' | Honeycomb sealing preferably for steam turbine |
| US6632069B1 (en) * | 2001-10-02 | 2003-10-14 | Oleg Naljotov | Step of pressure of the steam and gas turbine with universal belt |
| US20030194322A1 (en) * | 2002-04-16 | 2003-10-16 | Herbert Brandl | Moving blade for a turbomachine |
| US20040101410A1 (en) * | 2001-10-02 | 2004-05-27 | Oleg Naljotov | Axial flow fluid machine |
| US20040156722A1 (en) * | 2003-02-06 | 2004-08-12 | Kafu Chu | Method and apparatus to facilitate reducing steam leakage |
| US20050058539A1 (en) * | 2003-09-12 | 2005-03-17 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
| US20060133928A1 (en) * | 2004-12-22 | 2006-06-22 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
| US20060277922A1 (en) * | 2005-06-09 | 2006-12-14 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
| US20070040335A1 (en) * | 2005-08-22 | 2007-02-22 | General Electric Company | Axially adjustable sealing ring |
| US20070065277A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Centrifugal compressor including a seal system |
| US20070063449A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Stationary seal ring for a centrifugal compressor |
| US20070065276A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
| FR2927685A1 (en) * | 2008-02-18 | 2009-08-21 | Gen Electric | SEAL RING ASSEMBLY AND TURBINE ENGINE COMPRISING SUCH AN ASSEMBLY |
| US20110068540A1 (en) * | 2009-09-22 | 2011-03-24 | Colson Darryl A | Staggered seal assembly |
| US20110070072A1 (en) * | 2009-09-23 | 2011-03-24 | General Electric Company | Rotary machine tip clearance control mechanism |
| CN101220757B (en) * | 2007-01-09 | 2013-03-27 | 株式会社东芝 | Steam turbine |
| CN103184900A (en) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | Stage of a gas turbine engine and corresponding method of retrofitting |
| US20130189106A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Turbomachine blade tip shroud |
| US20130330179A1 (en) * | 2012-06-08 | 2013-12-12 | Rohit Chouhan | Shroud for a rotary machine and methods of assembling same |
| US20140079538A1 (en) * | 2012-09-11 | 2014-03-20 | Sanji Ekanayake | Replaceable seals for turbine engine components and methods for installing the same |
| US20140286766A1 (en) * | 2012-09-11 | 2014-09-25 | General Electric Company | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly |
| US20150176422A1 (en) * | 2012-06-25 | 2015-06-25 | Borgwarner Inc. | Exhaust-gas turbocharger |
| CN105408633A (en) * | 2013-07-09 | 2016-03-16 | 萨乐锐伊塔洛工业有限公司 | Adjustable cooling pump for internal combustion engine |
| US9885368B2 (en) | 2012-05-24 | 2018-02-06 | Carrier Corporation | Stall margin enhancement of axial fan with rotating shroud |
| US20180142567A1 (en) * | 2016-11-18 | 2018-05-24 | MTU Aero Engines AG | Sealing system for an axial turbomachine and axial turbomachine |
| FR3068070A1 (en) * | 2017-06-26 | 2018-12-28 | Safran Aircraft Engines | TURBINE FOR TURBOMACHINE |
| US10323537B2 (en) * | 2015-10-02 | 2019-06-18 | DOOSAN Heavy Industries Construction Co., LTD | Gas turbine tip clearance control assembly |
| CN111691927A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Turbine and turbine blade tip clearance seal structure |
| US20230019443A1 (en) * | 2019-12-12 | 2023-01-19 | Nuovo Pignone Tecnologie - S.R.L. | Composite seal structure for a machine, and method of manufacturing the composite seal structure |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5449407U (en) * | 1977-09-13 | 1979-04-05 | ||
| DE19738671B4 (en) * | 1997-09-04 | 2007-03-01 | Alstom | sealing arrangement |
| DE19850732A1 (en) | 1998-11-04 | 2000-05-11 | Asea Brown Boveri | Axial turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2416268A (en) * | 1943-10-01 | 1947-02-18 | Allis Chalmers Mfg Co | Hydraulic turbine seal |
| US2956733A (en) * | 1954-09-28 | 1960-10-18 | Stalker Corp | Fluid turning wheels for compressors |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE621436A (en) * | 1961-09-04 | 1962-08-16 |
-
1973
- 1973-09-27 US US401455A patent/US3867060A/en not_active Expired - Lifetime
-
1974
- 1974-07-29 CA CA205,865A patent/CA1004143A/en not_active Expired
- 1974-09-25 DE DE2445705A patent/DE2445705C2/en not_active Expired
- 1974-09-26 JP JP49110045A patent/JPS5757607B2/ja not_active Expired
- 1974-09-26 FR FR7432408A patent/FR2245852B1/fr not_active Expired
- 1974-09-26 IT IT27762/74A patent/IT1022359B/en active
- 1974-09-27 GB GB4215274A patent/GB1473719A/en not_active Expired
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Cited By (56)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2470269A1 (en) * | 1979-11-27 | 1981-05-29 | Snecma | RETENTION STRUCTURE FOR A COMPRESSOR CASE OF A TURBOMACHINE |
| EP0030179A1 (en) * | 1979-11-27 | 1981-06-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Retaining structure for the compressor housing of a turbo engine |
| FR2483008A1 (en) * | 1980-05-24 | 1981-11-27 | Mtu Muenchen Gmbh | DEVICE FOR MINIMIZING AND MAINTAINING CONSTANT EXTERMITY SETTING OF AXIAL TURBINE BLADES OF GAS TURBINE ENGINES |
| US4697978A (en) * | 1984-07-26 | 1987-10-06 | Matsushita Electric Industrial Co., Ltd. | Industrial robot |
| US4941801A (en) * | 1988-03-23 | 1990-07-17 | Aisin Seiki Kabushiki Kaisha | Double water pump device |
| US5037273A (en) * | 1988-12-19 | 1991-08-06 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Compressor impeller |
| US5362072A (en) * | 1992-12-21 | 1994-11-08 | Imo Industries, Inc., Quabbin Division | Turbine radial adjustable labyrinth seal |
| US5501573A (en) * | 1993-01-29 | 1996-03-26 | Steam Specialties, Inc. | Segmented seal assembly and method for retrofitting the same to turbines and the like |
| US5632598A (en) * | 1995-01-17 | 1997-05-27 | Dresser-Rand | Shrouded axial flow turbo machine utilizing multiple labrinth seals |
| WO2000058607A1 (en) * | 1999-03-31 | 2000-10-05 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie 'nauchno-Proizvodstvennoe Predpriyatie 'motor' | Honeycomb sealing preferably for steam turbine |
| US6632069B1 (en) * | 2001-10-02 | 2003-10-14 | Oleg Naljotov | Step of pressure of the steam and gas turbine with universal belt |
| US20040101410A1 (en) * | 2001-10-02 | 2004-05-27 | Oleg Naljotov | Axial flow fluid machine |
| US20030194322A1 (en) * | 2002-04-16 | 2003-10-16 | Herbert Brandl | Moving blade for a turbomachine |
| US6962484B2 (en) * | 2002-04-16 | 2005-11-08 | Alstom Technology Ltd | Moving blade for a turbomachine |
| US6776577B1 (en) * | 2003-02-06 | 2004-08-17 | General Electric Company | Method and apparatus to facilitate reducing steam leakage |
| US20040156722A1 (en) * | 2003-02-06 | 2004-08-12 | Kafu Chu | Method and apparatus to facilitate reducing steam leakage |
| US20050058539A1 (en) * | 2003-09-12 | 2005-03-17 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
| US6926495B2 (en) * | 2003-09-12 | 2005-08-09 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
| US7287956B2 (en) * | 2004-12-22 | 2007-10-30 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
| US20060133928A1 (en) * | 2004-12-22 | 2006-06-22 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
| US20060277922A1 (en) * | 2005-06-09 | 2006-12-14 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
| US7909569B2 (en) * | 2005-06-09 | 2011-03-22 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
| US20070040335A1 (en) * | 2005-08-22 | 2007-02-22 | General Electric Company | Axially adjustable sealing ring |
| US20070065277A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Centrifugal compressor including a seal system |
| US20070063449A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Stationary seal ring for a centrifugal compressor |
| US20070065276A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
| CN101220757B (en) * | 2007-01-09 | 2013-03-27 | 株式会社东芝 | Steam turbine |
| FR2927685A1 (en) * | 2008-02-18 | 2009-08-21 | Gen Electric | SEAL RING ASSEMBLY AND TURBINE ENGINE COMPRISING SUCH AN ASSEMBLY |
| JP2009191850A (en) * | 2008-02-18 | 2009-08-27 | General Electric Co <Ge> | Steam turbine engine and method of assembling the same |
| US20110068540A1 (en) * | 2009-09-22 | 2011-03-24 | Colson Darryl A | Staggered seal assembly |
| US8083236B2 (en) * | 2009-09-22 | 2011-12-27 | Hamilton Sundstrand Corporation | Staggered seal assembly |
| US20110070072A1 (en) * | 2009-09-23 | 2011-03-24 | General Electric Company | Rotary machine tip clearance control mechanism |
| US20130170962A1 (en) * | 2012-01-03 | 2013-07-04 | General Electric Company | Forward Step Honeycomb Seal for Turbine Shroud |
| US9476317B2 (en) | 2012-01-03 | 2016-10-25 | General Electric Company | Forward step honeycomb seal for turbine shroud |
| CN103184900A (en) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | Stage of a gas turbine engine and corresponding method of retrofitting |
| US9080459B2 (en) * | 2012-01-03 | 2015-07-14 | General Electric Company | Forward step honeycomb seal for turbine shroud |
| CN103184900B (en) * | 2012-01-03 | 2017-10-24 | 通用电气公司 | For turbine shroud to the cellular seal of front step |
| US20130189106A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Turbomachine blade tip shroud |
| US9109455B2 (en) * | 2012-01-20 | 2015-08-18 | General Electric Company | Turbomachine blade tip shroud |
| US9885368B2 (en) | 2012-05-24 | 2018-02-06 | Carrier Corporation | Stall margin enhancement of axial fan with rotating shroud |
| US20130330179A1 (en) * | 2012-06-08 | 2013-12-12 | Rohit Chouhan | Shroud for a rotary machine and methods of assembling same |
| US8936431B2 (en) * | 2012-06-08 | 2015-01-20 | General Electric Company | Shroud for a rotary machine and methods of assembling same |
| US10119411B2 (en) * | 2012-06-25 | 2018-11-06 | Borgwarner Inc. | Exhaust-gas turbocharger |
| US20150176422A1 (en) * | 2012-06-25 | 2015-06-25 | Borgwarner Inc. | Exhaust-gas turbocharger |
| US20140079538A1 (en) * | 2012-09-11 | 2014-03-20 | Sanji Ekanayake | Replaceable seals for turbine engine components and methods for installing the same |
| US9309776B2 (en) * | 2012-09-11 | 2016-04-12 | General Electric Company | Replaceable seals for turbine engine components and methods for installing the same |
| US20140286766A1 (en) * | 2012-09-11 | 2014-09-25 | General Electric Company | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly |
| CN105408633A (en) * | 2013-07-09 | 2016-03-16 | 萨乐锐伊塔洛工业有限公司 | Adjustable cooling pump for internal combustion engine |
| US10323537B2 (en) * | 2015-10-02 | 2019-06-18 | DOOSAN Heavy Industries Construction Co., LTD | Gas turbine tip clearance control assembly |
| US20180142567A1 (en) * | 2016-11-18 | 2018-05-24 | MTU Aero Engines AG | Sealing system for an axial turbomachine and axial turbomachine |
| FR3068070A1 (en) * | 2017-06-26 | 2018-12-28 | Safran Aircraft Engines | TURBINE FOR TURBOMACHINE |
| EP3421730A1 (en) * | 2017-06-26 | 2019-01-02 | Safran Aircraft Engines | Turbine for turbine engine with sealing ring comprising two parts |
| US10760441B2 (en) | 2017-06-26 | 2020-09-01 | Safran Aircraft Engines | Turbine for a turbine engine |
| US20230019443A1 (en) * | 2019-12-12 | 2023-01-19 | Nuovo Pignone Tecnologie - S.R.L. | Composite seal structure for a machine, and method of manufacturing the composite seal structure |
| US11927099B2 (en) * | 2019-12-12 | 2024-03-12 | Nuovo Pignone Tecnologie—S.R.L. | Composite seal structure for a machine, and method of manufacturing the composite seal structure |
| CN111691927A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Turbine and turbine blade tip clearance seal structure |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2245852B1 (en) | 1980-09-05 |
| GB1473719A (en) | 1977-05-18 |
| JPS5077704A (en) | 1975-06-25 |
| CA1004143A (en) | 1977-01-25 |
| JPS5757607B2 (en) | 1982-12-06 |
| IT1022359B (en) | 1978-03-20 |
| DE2445705A1 (en) | 1975-04-10 |
| FR2245852A1 (en) | 1975-04-25 |
| DE2445705C2 (en) | 1984-05-17 |
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