[go: up one dir, main page]

US3817655A - Stator blade mounting structure for turbomachines - Google Patents

Stator blade mounting structure for turbomachines Download PDF

Info

Publication number
US3817655A
US3817655A US00308882A US30888272A US3817655A US 3817655 A US3817655 A US 3817655A US 00308882 A US00308882 A US 00308882A US 30888272 A US30888272 A US 30888272A US 3817655 A US3817655 A US 3817655A
Authority
US
United States
Prior art keywords
blades
casing
mounting ring
bore
ring
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.)
Expired - Lifetime
Application number
US00308882A
Inventor
E Huesgen
C Geary
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Carrier Corp
Elliott Turbomachinery Co Inc
Original Assignee
Carrier Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Carrier Corp filed Critical Carrier Corp
Priority to US00308882A priority Critical patent/US3817655A/en
Application granted granted Critical
Publication of US3817655A publication Critical patent/US3817655A/en
Assigned to ELLIOTT TURBOMACHINERY CO., INC. reassignment ELLIOTT TURBOMACHINERY CO., INC. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: CARRIER CORPORATION, A CORP OF DEL.
Assigned to FIRST NATIONAL BANK OF CHICAGO, THE reassignment FIRST NATIONAL BANK OF CHICAGO, THE LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: ELLIOT TURBOMACHINERY CO., INC.
Assigned to CONTINENTAL BANK N.A. reassignment CONTINENTAL BANK N.A. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ELLIOTT TURBOMACHINERY CO., INC.
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • ABSTRACT The internal surface of the casing of a turbomachine is formed with an internal circular rib machined with a circular bore terminating at an inwardly extending radial flange.
  • the root portions of a circular series of stator blades are assembled in a blade mounting ring. The blades are restrained against axial and radial movement in the ring.
  • the mounting ring with the blades preassembled therein, is positioned in the casing bore and is fixed therein as by an annular member which is bolted to the casing in clamping engagement with the roots of the blades and serving to clamp the assembly in the casing.
  • the conventional method of fixedly mounting stator blades in a turbine casing consists of machining a circumferentially extending slot in the inner surface of the casing.
  • the slot is of T formation, or the like, and the roots of the stator blades are machined with a mating configuration so that the blades are interlocked with the casing.
  • the blades are inserted individually in the T slot. With that method, it is difficult to machine the T slots in large casings and hold the machined surfaces true. Such machining and assembly is time consuming and expensive. Also, an extensive amount of time is consumed in removing the blades for replacement.
  • This invention has'as an object a stator blade mounting structure which results in a very substantial reduction in machining and assembly time andwhich provides for the ready and convenient removal and replacement of the stator blades.
  • the turbine casing is formed with an internal circular rib.
  • the rib is formed with a radially disposed end surface and with a cylindrical bore terminating man inwardly extending flange.
  • a circular series of stator blades are assembled in a blade mounting ring. Means is provided for limiting movement of the assembled blades in axial and radial directions relative to the mounting ring.
  • the mounting ring is positioned in the circular casing bore and retained therein by means including bolts threaded into the radial end surface of the casing rib.
  • FIG. 1 is a partial sectional view of a turbine embodying our invention.
  • FIG. 2 is a view taken on line 22, FIG. 1.
  • the casing of the turbine is indicated at and is formed with an inlet passage 11 and an exhaust passage 12.
  • the casing is formed with an inwardly extending curved wall 13 defining in part the inlet 11.
  • a diffuser section 1 4 is attached to the casing 10 as by screws, one of which is shown at 15, and forms in part the exhaust passage 12.
  • the casing 10 is formed intermediate the inlet and outlet passages 11 and 12 with an internal circular rib 17.
  • the rib 17 is formed with a radially disposed end surface 18 and with a cylindrical bore 20 extending from the end surface 18 and terminating at an inwardly extending radial flange 21.
  • a stator blade mounting ring 22 is positioned in the bore 20and a circularseries of stator blades is mounted in the ring 22,, see FIG. 2.
  • stator blades 25 are preassembled in the ring 22.
  • the ring 22 is formed with a radial flange 23.
  • the flange 23 of ring 22 is formed, on the surface confronting the stator blades 25, with a circular rib 30.
  • the confronting surfaces of the blades 25 are formed with complemental notches whereby the blades 25' are restrained against radial movement relative to the ring 22.
  • Means is also provided to limit axial displacement of the preassembled blades 25 relative to the ring 22.
  • the ring 22 is formed with a series of threaded apertures in which screws 33 are threaded.
  • the inner ends of the screws 33 extend into apertures formed in the roots of the blades 25. These apertures are enlarged relative to the diameter of the screws 33 to permit limited movement of the blades axially in the ring 22, but the arrangement is effective to prevent detachment of the preassembled blades from the mounting ring 22.
  • the mounting ring 22 with the stator blades 25 preassembled therein is mounted in the bore 20 of the casing rib 17.
  • Means is provided for fixedly securing the blades 25 in the mounting ring and the ring in the rib 17.
  • the securing means is in the form of an annular member 35 detachably secured to rib 17 of the casing by a series of screws 37 extending through the ring 35 and threaded into the rib 17.
  • the axial dimension of the ring 22 is less than the axial length of the bore 20.
  • the mounting ring 35 is formed with cylindrical portion 40 dimensioned for a close fit in the portion of the bore 20 outwardly of the ring 22 as shown in FIG. 1.
  • the ring 35 is formed with an annular surface abutting against the stator blades 25. Accordingly, when the bolts 37 are tightened, the blades 25 are clamped against the flange 23 of ring 22 and the ring 22 clamped against the flange 21 of the rib 17.
  • the turbine blade carrying disc 43 is fixedly mounted on the shaft 45.
  • the inner portions of the wall sections 13, 14 are formed with cylindrical bores to receive labyrinth sealing ring structures 50 engaging the shaft 45.
  • the rotor disc 43 carries a circular series of turbine blades 51 which are positioned on the downstream side of the stator blades 25 in adjacency thereto.
  • the securing ring 35 is formed with a shroud portion 57 encircling the tips of the turbine blades 51.
  • a stator blade mounting structure for turbomachines comprising a machine casing formed with a circular bore, a stator blade mounting ring positioned in said bore, a circular series of stator blades having root portions mounted in said mounting ring, said blades extending radially inwardly from said ring, securing means carried by said casing and engaging said blades for fixedly securing said blades in said mounting ring and fixedly clamping said mounting ring in said casing bore.
  • a stator blade mounting structure for turbomachines comprising a machine casing formed with an internal circular rib having a radial end surface, said rib being formed with a cylindrical bore extending from said end surface and terminating at an inwardly extending radial flange, a stator blade mounting ring positioned in said rib bore and having an inwardly extending radial flange abutting against said radial flange of said bore, a circular series of stator blades having root portions mounted in said mounting ring and extending radially inwardly therefrom, securing means detachably secured to said casing and engaging the root portions of said blades and operable to fixedly secure said

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The internal surface of the casing of a turbomachine is formed with an internal circular rib machined with a circular bore terminating at an inwardly extending radial flange. The root portions of a circular series of stator blades are assembled in a blade mounting ring. The blades are restrained against axial and radial movement in the ring. The mounting ring, with the blades preassembled therein, is positioned in the casing bore and is fixed therein as by an annular member which is bolted to the casing in clamping engagement with the roots of the blades and serving to clamp the assembly in the casing.

Description

United States Patent Huesgen et al.
[ June 18, 1974 STATOR BLADE MOUNTING STRUCTURE FOR TURBOMACHINES Carrier Corporation, Syracuse, NY.
Nov. 22, 1972 US. Cl. 415/217, 415/219 R Int. Cl. Fold l/02 [56] References Cited UNITED STATES PATENTS 2,935,296 5/1960 Hockert et al 416/220 FOREIGN PATENTS OR APPLICATIONS 776,988 6/1957 Great Britain 415/217 Field of Search 415/199 R,2l6,217,2l8,
1,010,300 11/1965 GreatBritain 415/218 Primary Examinerl-lenry F. Raduazo Attorney, Agent, or Firm.l. Raymond Curtin [57] ABSTRACT The internal surface of the casing of a turbomachine is formed with an internal circular rib machined with a circular bore terminating at an inwardly extending radial flange. The root portions of a circular series of stator blades are assembled in a blade mounting ring. The blades are restrained against axial and radial movement in the ring. The mounting ring, with the blades preassembled therein, is positioned in the casing bore and is fixed therein as by an annular member which is bolted to the casing in clamping engagement with the roots of the blades and serving to clamp the assembly in the casing.
4 Clains, 2 Drawing Figures I r tutti .LL '7 33 37 j a 22 40 I4 I I3 K all/ qlIll/l/l/(Z/ a STATOR BLADE MOUNTING STRUCTURE FOR TURBOMACHINES BACKGROUND OF THE INVENTION The conventional method of fixedly mounting stator blades in a turbine casing consists of machining a circumferentially extending slot in the inner surface of the casing. The slot is of T formation, or the like, and the roots of the stator blades are machined with a mating configuration so that the blades are interlocked with the casing. The blades are inserted individually in the T slot. With that method, it is difficult to machine the T slots in large casings and hold the machined surfaces true. Such machining and assembly is time consuming and expensive. Also, an extensive amount of time is consumed in removing the blades for replacement.
This invention has'as an object a stator blade mounting structure which results in a very substantial reduction in machining and assembly time andwhich provides for the ready and convenient removal and replacement of the stator blades.
SUMMARY OF THE INVENTION The turbine casing is formed with an internal circular rib. The rib is formed with a radially disposed end surface and with a cylindrical bore terminating man inwardly extending flange. A circular series of stator blades are assembled in a blade mounting ring. Means is provided for limiting movement of the assembled blades in axial and radial directions relative to the mounting ring. The mounting ring is positioned in the circular casing bore and retained therein by means including bolts threaded into the radial end surface of the casing rib.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a partial sectional view of a turbine embodying our invention; and
FIG. 2 is a view taken on line 22, FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT In the turbine structure shown in FIG. 1, the casing of the turbine is indicated at and is formed with an inlet passage 11 and an exhaust passage 12. The casing is formed with an inwardly extending curved wall 13 defining in part the inlet 11. A diffuser section 1 4 is attached to the casing 10 as by screws, one of which is shown at 15, and forms in part the exhaust passage 12.
The casing 10 is formed intermediate the inlet and outlet passages 11 and 12 with an internal circular rib 17. The rib 17 is formed with a radially disposed end surface 18 and with a cylindrical bore 20 extending from the end surface 18 and terminating at an inwardly extending radial flange 21. A stator blade mounting ring 22 is positioned in the bore 20and a circularseries of stator blades is mounted in the ring 22,, see FIG. 2.
In practice, the stator blades 25 are preassembled in the ring 22. In the structure shown, the ring 22 is formed with a radial flange 23. The flange 23 of ring 22 is formed, on the surface confronting the stator blades 25, with a circular rib 30. The confronting surfaces of the blades 25 are formed with complemental notches whereby the blades 25' are restrained against radial movement relative to the ring 22.
Means is also provided to limit axial displacement of the preassembled blades 25 relative to the ring 22. The ring 22 is formed with a series of threaded apertures in which screws 33 are threaded. The inner ends of the screws 33 extend into apertures formed in the roots of the blades 25. These apertures are enlarged relative to the diameter of the screws 33 to permit limited movement of the blades axially in the ring 22, but the arrangement is effective to prevent detachment of the preassembled blades from the mounting ring 22.
The mounting ring 22 with the stator blades 25 preassembled therein is mounted in the bore 20 of the casing rib 17. Means is provided for fixedly securing the blades 25 in the mounting ring and the ring in the rib 17. Referring to FIG. 1 of the drawings, the securing means is in the form of an annular member 35 detachably secured to rib 17 of the casing by a series of screws 37 extending through the ring 35 and threaded into the rib 17. The axial dimension of the ring 22 is less than the axial length of the bore 20. The mounting ring 35 is formed with cylindrical portion 40 dimensioned for a close fit in the portion of the bore 20 outwardly of the ring 22 as shown in FIG. 1. The ring 35 is formed with an annular surface abutting against the stator blades 25. Accordingly, when the bolts 37 are tightened, the blades 25 are clamped against the flange 23 of ring 22 and the ring 22 clamped against the flange 21 of the rib 17.
The turbine blade carrying disc 43 is fixedly mounted on the shaft 45. The inner portions of the wall sections 13, 14 are formed with cylindrical bores to receive labyrinth sealing ring structures 50 engaging the shaft 45.
The rotor disc 43 carries a circular series of turbine blades 51 which are positioned on the downstream side of the stator blades 25 in adjacency thereto.
The securing ring 35 is formed with a shroud portion 57 encircling the tips of the turbine blades 51.
While we have described a preferred embodiment of our invention, it should be understood that the invention is not limited thereto, but may be otherwise embodied within the scope of the following claims.
We claim:
1. A stator blade mounting structure for turbomachines comprising a machine casing formed with a circular bore, a stator blade mounting ring positioned in said bore, a circular series of stator blades having root portions mounted in said mounting ring, said blades extending radially inwardly from said ring, securing means carried by said casing and engaging said blades for fixedly securing said blades in said mounting ring and fixedly clamping said mounting ring in said casing bore.
2. A stator blade mounting structure as defined in claim 1 and including means carried by said mounting ring and cooperable with the root portion of each of said blades initially assembled in said mounting ring to permit limited movement of the blades in a direction axially of said ring.
3. A stator blade mounting structure for turbomachines comprising a machine casing formed with an internal circular rib having a radial end surface, said rib being formed with a cylindrical bore extending from said end surface and terminating at an inwardly extending radial flange, a stator blade mounting ring positioned in said rib bore and having an inwardly extending radial flange abutting against said radial flange of said bore, a circular series of stator blades having root portions mounted in said mounting ring and extending radially inwardly therefrom, securing means detachably secured to said casing and engaging the root portions of said blades and operable to fixedly secure said

Claims (4)

1. A stator blade mounting structure for turbomachines comprising a machine casing formed with a circular bore, a stator blade mounting ring positioned in said bore, a circular series of stator blades having root portions mounted in said mounting ring, said blades extending radially inwardly from said ring, securing means carried by said casing and engaging said blades for fixedly securing said blades in said mounting ring and fixedly clamping said mounting ring in said casing bore.
2. A stator blade mounting structure as defined in claim 1 and including means carried by said mounting ring and cooperable with the root portion of each of said blades initially assembled in said mounting ring to permit limited movement of the blades in a direction axially of said ring.
3. A stator blade mounting structure for turbomachines comprising a machine casing formed with an internal circular rib having a radial end surface, said rib being formed with a cylindrical bore extending from said end surface and terminating at an inwardly extending radial flange, a stator blade mounting ring positioned in said rib bore and having an inwardly extending radial flange abutting against said radial flange of said bore, a circular series of stator blades having root portions mounted in said mounting ring and extending radially inwardly therefrom, securing means detachably secured to said casing and engaging the root portions of said blades and operable to fixedly secure said blades in said mounting ring and said mounting ring in said casing bore.
4. A stator blade mounting structure as defined in claim 3 wherein said securing means includes an annular member secured to said end surface of said casing rib.
US00308882A 1972-11-22 1972-11-22 Stator blade mounting structure for turbomachines Expired - Lifetime US3817655A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US00308882A US3817655A (en) 1972-11-22 1972-11-22 Stator blade mounting structure for turbomachines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00308882A US3817655A (en) 1972-11-22 1972-11-22 Stator blade mounting structure for turbomachines

Publications (1)

Publication Number Publication Date
US3817655A true US3817655A (en) 1974-06-18

Family

ID=23195779

Family Applications (1)

Application Number Title Priority Date Filing Date
US00308882A Expired - Lifetime US3817655A (en) 1972-11-22 1972-11-22 Stator blade mounting structure for turbomachines

Country Status (1)

Country Link
US (1) US3817655A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4630994A (en) * 1983-09-16 1986-12-23 Motoren-Und Turbinen Union Munchen Gmbh Apparatus for axially and circumferentially locking stationary casing components of turbomachines
US4900223A (en) * 1989-02-21 1990-02-13 Westinghouse Electric Corp Steam turbine
US5492445A (en) * 1994-02-18 1996-02-20 Solar Turbines Incorporated Hook nozzle arrangement for supporting airfoil vanes
US5564897A (en) * 1992-04-01 1996-10-15 Abb Stal Ab Axial turbo-machine assembly with multiple guide vane ring sectors and a method of mounting thereof
US5575621A (en) * 1994-10-14 1996-11-19 Abb Management Ag Compressor with a guide vane fastening arrangement
US6318961B1 (en) * 1998-11-04 2001-11-20 Asea Brown Boveri Ag Axial turbine
US20100278651A1 (en) * 2008-01-15 2010-11-04 Abb Turbo Systems Ag Guide device

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB776988A (en) * 1954-10-07 1957-06-12 British Thomson Houston Co Ltd Means for fixing nozzles in turbine casings
US2935296A (en) * 1951-12-26 1960-05-03 Gen Motors Corp Blade retaining means
GB1010300A (en) * 1962-01-25 1965-11-17 Rateau Soc Elastic-fluid turbines with multiple casings

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935296A (en) * 1951-12-26 1960-05-03 Gen Motors Corp Blade retaining means
GB776988A (en) * 1954-10-07 1957-06-12 British Thomson Houston Co Ltd Means for fixing nozzles in turbine casings
GB1010300A (en) * 1962-01-25 1965-11-17 Rateau Soc Elastic-fluid turbines with multiple casings

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4630994A (en) * 1983-09-16 1986-12-23 Motoren-Und Turbinen Union Munchen Gmbh Apparatus for axially and circumferentially locking stationary casing components of turbomachines
US4900223A (en) * 1989-02-21 1990-02-13 Westinghouse Electric Corp Steam turbine
US5564897A (en) * 1992-04-01 1996-10-15 Abb Stal Ab Axial turbo-machine assembly with multiple guide vane ring sectors and a method of mounting thereof
US5492445A (en) * 1994-02-18 1996-02-20 Solar Turbines Incorporated Hook nozzle arrangement for supporting airfoil vanes
US5575621A (en) * 1994-10-14 1996-11-19 Abb Management Ag Compressor with a guide vane fastening arrangement
CN1057820C (en) * 1994-10-14 2000-10-25 Abb阿尔斯托姆电力(瑞士)股份有限公司 Compressor
US6318961B1 (en) * 1998-11-04 2001-11-20 Asea Brown Boveri Ag Axial turbine
US20100278651A1 (en) * 2008-01-15 2010-11-04 Abb Turbo Systems Ag Guide device
US8251647B2 (en) * 2008-01-15 2012-08-28 Abb Turbo Systems Ag Guide device

Similar Documents

Publication Publication Date Title
US4664599A (en) Two stage turbine rotor assembly
US3023998A (en) Rotor blade retaining device
US3356339A (en) Turbine rotor
EP0548724B1 (en) Compressor of turbine blade manufacture
US3867060A (en) Shroud assembly
US3814539A (en) Rotor sealing arrangement for an axial flow fluid turbine
US6575703B2 (en) Turbine disk side plate
US6283712B1 (en) Cooling air supply through bolted flange assembly
US5052891A (en) Connection for gas turbine engine rotor elements
US3056583A (en) Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US4668167A (en) Multifunction labyrinth seal support disk for a turbojet engine rotor
US5913660A (en) Gas turbine engine fan blade retention
US20070122270A1 (en) Turbomachine, especially a gas turbine
GB904138A (en) Improvements in or relating to stator structures, for example for axial flow gas turbine engines
US3824030A (en) Diaphragm and labyrinth seal assembly for gas turbines
US7828521B2 (en) Turbine module for a gas-turbine engine
US3817655A (en) Stator blade mounting structure for turbomachines
US3990812A (en) Radial inflow blade cooling system
GB1528421A (en) Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance
RU2604475C2 (en) Unlockable device for locking axial direction of sealing ring being in contact with impulse rotor wheel of aircraft turbine machine
US3765795A (en) Compositely formed rotors and their manufacture
GB867759A (en) Stator vane assemblies for axial-flow compressors or turbines
US7507072B2 (en) Turbine module for a gas-turbine engine with rotor that includes a monoblock body
CN207620852U (en) Baffle assembly with preswirl device
JPH0639884B2 (en) Turbin Shaft Seal Assembly

Legal Events

Date Code Title Description
AS Assignment

Owner name: ELLIOTT TURBOMACHINERY CO., INC., A CORP OF DELAWA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. SUBJECT TO LICENSE RECITED.;ASSIGNOR:CARRIER CORPORATION, A CORP OF DEL.;REEL/FRAME:004499/0922

Effective date: 19851220

AS Assignment

Owner name: FIRST NATIONAL BANK OF CHICAGO, THE, ONE FIRST NAT

Free format text: LICENSE;ASSIGNOR:ELLIOT TURBOMACHINERY CO., INC.;REEL/FRAME:004940/0562

Effective date: 19871109

Owner name: FIRST NATIONAL BANK OF CHICAGO, THE,ILLINOIS

Free format text: LICENSE;ASSIGNOR:ELLIOT TURBOMACHINERY CO., INC.;REEL/FRAME:004940/0562

Effective date: 19871109

AS Assignment

Owner name: CONTINENTAL BANK N.A.

Free format text: SECURITY INTEREST;ASSIGNOR:ELLIOTT TURBOMACHINERY CO., INC.;REEL/FRAME:005258/0092

Effective date: 19891212