EP0054116A1 - Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage - Google Patents
Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage Download PDFInfo
- Publication number
- EP0054116A1 EP0054116A1 EP19810107994 EP81107994A EP0054116A1 EP 0054116 A1 EP0054116 A1 EP 0054116A1 EP 19810107994 EP19810107994 EP 19810107994 EP 81107994 A EP81107994 A EP 81107994A EP 0054116 A1 EP0054116 A1 EP 0054116A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- housing
- diaphragm
- section
- rotor
- turbomachine
- 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.)
- Granted
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
Definitions
- This invention generally relates to rotary machines, and more specifically to stator blade assemblies thereof.
- rotor or stator blades of a rotary machine such as a compressor or expander must be removed from the machine for cleaning, maintenance, or replacement.
- rotary machines are often used with fluids containing a significant amount of particulates or debris. Over an extended period, these particulates and debris may accumulate on or erode the blade surfaces, necessitating periodic removal of the rotor or stator blades from the machine to clean or replace the blade surfaces. Routine inspection and maintenance, for example to repair or realign a rotor seal or blade, may also require removal of the rotor or stator blades from the machine.
- the present invention relates to a turbomachine having a stator blade assembly which may be easily installed in and removed from the turbomachine.
- this invention relates to a turbomachine comprising bladed rotor means including axially spaced first and second stage rotor blade rows; an inlet duct for directing a fluid past the bladed rotor means, and including an outwardly projecting duct flange; and a fluid casing for receiving fluid flowing past the bladed rotor means, and including an outwardly projecting casing flange.
- the turbomachine further comprises a stator blade assembly including stator blade means axially located between the first and second stage rotor blade rows, and outwardly projecting flanges positioned contiguous to the duct and casing flanges; and means for releasably securing the stator blade assembly to the fluid casing and the inlet duct.
- Machine 10 such as a multi-stage turbine incorporating teachings of the present invention.
- Machine 10 includes an axially extending rotor 12, first and second stage rotor blades 14 and 16, inlet duct 18, fluid casing 20, and stator blade assembly 22.
- Assembly 22 comprises housing 24, diaphragm 26, stator blades 30, and connecting means 32, discussed in greater detail below.
- Fluid casing 20 annularly extends around rotor 12, and rotor blades 14 and 16 are rigidly secured to rotor 12 and radially extend outward therefrom, forward to the left as viewed in Figure 1, of the fluid casing.
- two axially-spaced sets of rotor blades 14 and 16 are shown in Figure 1, it will be apparent to those skilled in the art that the present invention may be employed with a rotary compressor or expander having more than two spaced sets of rotor blades.
- Housing 24 is located between fluid casing 20 and inlet duct 18 and annularly extends around rotor blades 14 and 16, stator blades 30, and diaphragm 26.
- housing 24 is comprised of separable annular rings 34 and 36, and these rings are comprised of separable upper and lower sections, which preferably are both of semi-annular form disengagably joined together, for example by bolts, along adjacent horizontal flanges.
- band 34 includes top section 34a and bottom section 34b
- band 36 includes top section 36a and bottom section 36b. Rings 34 and 36 are releasably joined together, to fluid casing 20, and to inlet duct 18.
- front, outwardly extending flange portion 38 of band 34 is bolted to contiguous flange portion 40 of inlet duct 18; back, outwardly extending flange portion 42 of band 36 is bolted to contiguous flange portion 44 of fluid casing 20; and bands 34 and 36 are bolted together along adjacent, intermediate flanges 46 and 48.
- seals may be disposed between contiguous surfaces of inlet duct 18, fluid casing 20, and housing 24 to inhibit or to retard fluid flow between these surfaces.
- Diaphragm 26 is disposed within housing 24 and preferably is radially spaced therefrom to allow radial expansion and contraction of the diaphragm.
- Diaphragm 26 annularly extends around rotor blades 14 and 16 and comprises separable upper and lower diaphragm sections 50 and 52, which also preferably are both of semi-annular form disengagably joined together along a horizontal split line in any suitable manner such as by bolts.
- Stator blades 30 are secured to diaphragm 26 in any conventional manner and radially extend inward therefrom, between rotor blade rows 14 and 16.
- a horizontal split sealing member 54 is conventionally secure to stator blades 30 and radially extends inward therefrom substantially to impeller rotor 12 to inhibit fluid flow through the area between the rotor and the stator blades.
- Connecting means 32 releasably connects diaphragm 26 to housing 24 and limits relative rotation therebetween.
- connecting means 32 includes inside rib portion 56 of housing band 36, annular ring 58, and one or more pins 60.
- Ring 58 which may be integral with rib 56, axially extends from the rib, radially outside diaphragm 26, and pins 60 extend through ring 58 into engagement with diaphragm 26 to prevent substantially relative rotation between the diaphragm and ring 58.
- ring 58 defines a plurality of pin holes 62, for example 8 or 12 equally spaced about the ring; diaphragm 26 defines a like number of diaphragm sockets 64, with sockets 64 aligned with pin holes 62; and pins 60 extend through holes 62 and into sockets 64 to engage securely the diaphragm.
- set screws 66 may be threaded into diaphragm 26 to engage cooperating annular recesses (not shown) of pins 60, releasably maintaining pins 60 in position, as shown in Figure 1.
- upper portions of pins 60 may define threaded pin sockets 68 to facilitate moving the pins into and out of diaphragm sockets 64.
- abutting contact between pins 60 and the surfaces of ring 58 defining pin holes 62 substantially prevents rotational or axial movement of diaphragm 26.
- Rearward axial movement of diaphragm 26 is further prevented by rib 56 or, preferably, by a seal (not shown) which may be axially located between rib 56 and outside flange 70 of the diaphragm.
- rib 56 provides radial support for diaphragm 26 within housing 24.
- diaphragm 26 and stator blades 30 are supported .and largely held in place within housing 24, although pins 60 allow and, in fact, guide radial expansion and contraction of the diaphragm.
- housing 24 defines one or more radially extending housing apertures 72, pins 60 radially extend through apertures 72 and into diaphragm sockets 64, and covers 72 are disengagably secured to housing 24 and extend over pins 60 to limit radially outward movement thereof.
- Annular rib 76 extends inward from housing 24, and abutting contact between diaphragm 26 and rib 76 limits axially rearward movement-of the diaphragm.
- covers 72 comprise pin caps which extend into housing apertures 72, encircle and cover pins 60, and threadably engage the surfaces of housing 24 defining the housing apertures.
- covers 72 comprise flange portions which are integral with pins 60. These covers 72 are located outside housing 24, overlay housing apertures 72 and pins 60, and are releasably secured to housing 24 via bolts 78. With this latter embodiment, 0-rings may be disposed between flange covers 72 and housing 24, encircling pins 60.
- housing 24 may form an integral portion of inlet duct 18, and preferably the housing comprises an integral band portion encircling diaphragm 26 and stator blades 30.
- diaphragm 26 and stator blades 30 are supported within housing 24 via inside rib portion 80 of fluid casing 20, annular ring 82, and one or more pins 60.
- Annular ring 82 is separable from rib portion 80, and preferably is bolted thereto.
- ring 82 preferably defines a plurality of pin holes 62, with pins 60 extending through these holes and into diaphragm sockets 64, and set screws 66 may be used to maintain releasably pins 60 in sockets 64.
- a fluid is induced to flow through inlet duct 18 and past blades 14 and 16. If machine 10 is a compressor, then rotor blade rows 14 and 16 are rotated to compress the fluid flowing therepast. Alternately, if machine 10 is an expander, then the fluid causes rotation of blade rows 14 and 16. In either case, the fluid flows past blades 14 and 16, through fluid casing 20, and thence is discharged from machine 10.
- stator blade assembly 22 described above may be both removed from and installed in machine 10 in a relatively fast and inexpensive manner.
- top and bottom sections 34a and 34b of housing ring 34 are disconnected from each other. Then housing band 34 is disconnected from inlet duct 18 and housing band 36, and band 34 is removed from machine 10. Set screws 66 are loosened or removed and pins 60 are pulled out of diaphragm sockets 64, freeing housing band 36 from diaphragm 26. Top and bottom sections 36a and 36b of housing ring 36 are disconnected from each other, the whole band 36 is disconnected from casing 20, and band 36 is removed. With housing 24 thus removed, top and bottom sections 50 and 52 of diaphragm 26 are disengaged from each other and taken away from machine 10.
- pin covers 74 are first disconnected from housing 24 and removed, either by removing bolts 78 of Figure 1A or by unthreading the pin caps of Figure 1B from housing apertures 72.
- pins 60 are pulled out of diaphragm sockets 64 when pin covers 74 are pulled away from housing 24.
- pins 60 are manually pulled out of diaphragm sockets 64, via housing apertures 72, after covers 74 are removed.
- housing 24 is free of diaphragm 26 and stator blades 30; and thence the top and bottom sections of the housing are disconnected from each other, disconnected from inlet duct 18 and fluid casing 20, and then removed from machine. Lastly, top and bottom sections 50 and 52 of diaphragm 26 are disconnected from each other and taken from machine 10.
- stator housing assembly 22 may be removed without removing either inlet duct 18 or fluid casing 20.
- flanges 42 and 44 are first disconnected, freeing housing 24 and inlet duct 18 from fluid casing 20.
- Inlet duct 18, including annular housing portion 24, is then removed.
- Set screws 66 are loosened or removed, and then pins 60 are removed.
- Ring 82 is then disconnected from rib 80 and removed.
- Top and bottom sections 50 and 52 of diaphragm 26 are then disengaged from each other and radially moved out of machine 10.
- stator blade assembly 22 may be utilized to remove stator blade assembly 22 from machine 10, and one arrangement for removing and installing the stator blade assembly 22 shown in Figure 1B will be described herein in detail.
- posts 102 including support platforms 104 and top flanges 106, are positioned adjacent to the stator blade assembly, with top flanges 106 overlaying portions of flanges 108 of lower housing section 24b.
- Flanges 106 and 108 are then secured together by any conventional means wherein posts 102 provide additional support for stator blade assembly 22.
- guide rods Preferably, guide rods.
- inlet duct 18 is disengaged from the stator blade assembly and removed in any suitable manner, for example by an overhead crane.
- Pin covers 72 and pins 60 connecting upper diaphragm section with upper housing section 24a are removed, freeing this housing section from diaphragm 26.
- Upper housing section 24a is then disengaged from lower housing section 24b and from fluid casing 20 and removed in any conventional manner, again for example by an overhead crane.
- Upper diaphragm section 50 is then disengaged from lower diaphragm section 52 and also removed in any conventional manner such as by an overhead crane.
- Rails 112 are positioned adjacent machine 10, extending forward thereof between posts 102. Screw jacks 114, having top plates 116, are placed on platforms 104 of posts 102, and the screw jacks are extended to bring plates 116 into abutting contact with flanges 108 of lower housing section 24b. Lower housing section 24b is disengaged from fluid casing 20, and flanges 108 are disengaged from flanges 106. Lower housing and diaphragm sections 24b and 52 are now free to move downward; and by retracting screw jacks 114, plates 116, housing section 24b, and diaphragm section 52 are lowered toward rails 112. Before housing section 24b engages rails 112, wheels 120, 122, and 124 are secured to the lower housing section in any suitable manner to support diaphragm section 52 and housing section 24b for movement along the rails.
- Lower diaphragm section 52 with a plurality of stator blades 30 secured thereto and radially extending inward therefrom and with the lower half of sealing member 54 secured to and radially extending inward from these stator blades, is positioned within lower housing section 24b, slightly spaced therefrom.
- Diaphragm and housing sections 52 and 24b are connected together by inserting pins 60 through housing apertures 72 and into diaphragm sockets 64 and securing pin covers 72 to housing 24, locking the pins in place.
- Wheels 120, 122, and 124 are secured to lower housing section 24b.
- Diaphragm and housing sections 52 and 24b and wheels 120, 122, and 124 are mounted on rails 112 and moved therealong until the lower diaphragm and housing sections are adjacent fluid casing 20 and below rotor 12, as shown in Figure 5.
- Posts 102 are located outside rails 112, with flanges 108 of lower housing section 24b directly between support platforms 104 and top flanges 106.
- Guide rods 110 are inserted through flanges 108 and 106.
- Screw jacks 114 are positioned on platforms 104 and extended to bring plates 116 into abutting contact with flanges 108 and raise lower housing section 24b off rails 112. Wheels 120, 122, and 124 are removed from lower housing section 24b.
- Screw jacks 112 are extended to raise housing section 24b and diaphragm section 52 into their assembled positions and bring flanges 108 into abutting contact with top flanges 106.
- Flanges 106 and 108 are joined together, guide rods 110 are removed, and lower housing section 24b is disengagably secured to fluid casings 20.
- Rails 112 may be removed.
- Upper diaphragm section 50 also with a plurality of stator blades 30 secured thereto and with the upper half of sealing member 54 secured to these stator blades, is positioned, for example via an overhead crane, over lower diaphragm section 52 and rotor 12, and the upper and lower diaphragm sections are disengagably secured. together, forming diaphragm 26.
- Upper housing section 24a is positioned over diaphragm 26, again for example by an overhead crane, and disengagably secured to both lower housing section 24b and fluid casing 20.
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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US20209180A | 1980-10-30 | 1980-10-30 | |
US202091 | 1980-10-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0054116A1 true EP0054116A1 (de) | 1982-06-23 |
EP0054116B1 EP0054116B1 (de) | 1986-09-10 |
Family
ID=22748465
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19810107994 Expired EP0054116B1 (de) | 1980-10-30 | 1981-10-06 | Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0054116B1 (de) |
JP (1) | JPS5925092B2 (de) |
DE (1) | DE3175308D1 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1052377A3 (de) * | 1999-05-14 | 2002-11-13 | General Electric Company | Einrichtung und Methode zur Montage und Justierung eines Innengehäuses im Aussengehäuse einer Turbine |
EP1273760A1 (de) * | 2000-05-10 | 2003-01-08 | General Motors Corporation | Turbolader mit Leitschaufelkranzankoppelung |
GB2461163A (en) * | 2008-06-24 | 2009-12-30 | Rolls Royce Plc | Manufacturing a rotating blade assembly. |
RU2451793C1 (ru) * | 2010-12-20 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Турбина газотурбинного двигателя |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012211950A1 (de) * | 2012-07-09 | 2014-05-08 | Abb Turbo Systems Ag | Abgasturbine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1692537A (en) * | 1923-08-02 | 1928-11-20 | Westinghouse Electric & Mfg Co | Elastic-fluid turbine |
GB679916A (en) * | 1949-04-29 | 1952-09-24 | Geoffrey Bertram Robert Feilde | Improvements in gas turbines |
US2828105A (en) * | 1955-07-28 | 1958-03-25 | Vickers Armstrongs Ltd | Turbines |
GB815032A (en) * | 1956-03-27 | 1959-06-17 | Maschf Augsburg Nuernberg Ag | Improvements in or relating to multi-stage axial-flow turbines and compressors |
US2960306A (en) * | 1956-01-16 | 1960-11-15 | Gen Motors Corp | Turbine |
US3169748A (en) * | 1962-12-06 | 1965-02-16 | Westinghouse Electric Corp | Turbine apparatus |
US3628884A (en) * | 1970-06-26 | 1971-12-21 | Westinghouse Electric Corp | Method and apparatus for supporting an inner casing structure |
-
1981
- 1981-10-06 EP EP19810107994 patent/EP0054116B1/de not_active Expired
- 1981-10-06 DE DE8181107994T patent/DE3175308D1/de not_active Expired
- 1981-10-29 JP JP17219181A patent/JPS5925092B2/ja not_active Expired
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1692537A (en) * | 1923-08-02 | 1928-11-20 | Westinghouse Electric & Mfg Co | Elastic-fluid turbine |
GB679916A (en) * | 1949-04-29 | 1952-09-24 | Geoffrey Bertram Robert Feilde | Improvements in gas turbines |
US2828105A (en) * | 1955-07-28 | 1958-03-25 | Vickers Armstrongs Ltd | Turbines |
US2960306A (en) * | 1956-01-16 | 1960-11-15 | Gen Motors Corp | Turbine |
GB815032A (en) * | 1956-03-27 | 1959-06-17 | Maschf Augsburg Nuernberg Ag | Improvements in or relating to multi-stage axial-flow turbines and compressors |
US3169748A (en) * | 1962-12-06 | 1965-02-16 | Westinghouse Electric Corp | Turbine apparatus |
US3628884A (en) * | 1970-06-26 | 1971-12-21 | Westinghouse Electric Corp | Method and apparatus for supporting an inner casing structure |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1052377A3 (de) * | 1999-05-14 | 2002-11-13 | General Electric Company | Einrichtung und Methode zur Montage und Justierung eines Innengehäuses im Aussengehäuse einer Turbine |
EP1273760A1 (de) * | 2000-05-10 | 2003-01-08 | General Motors Corporation | Turbolader mit Leitschaufelkranzankoppelung |
GB2461163A (en) * | 2008-06-24 | 2009-12-30 | Rolls Royce Plc | Manufacturing a rotating blade assembly. |
GB2461163B (en) * | 2008-06-24 | 2010-08-18 | Rolls Royce Plc | A method of forming a rotating blade assembly |
RU2451793C1 (ru) * | 2010-12-20 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Турбина газотурбинного двигателя |
Also Published As
Publication number | Publication date |
---|---|
JPS57105504A (en) | 1982-07-01 |
DE3175308D1 (en) | 1986-10-16 |
EP0054116B1 (de) | 1986-09-10 |
JPS5925092B2 (ja) | 1984-06-14 |
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