US3689174A - Axial flow turbine structure - Google Patents

Axial flow turbine structure Download PDF

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Publication number
US3689174A
US3689174A US105551A US3689174DA US3689174A US 3689174 A US3689174 A US 3689174A US 105551 A US105551 A US 105551A US 3689174D A US3689174D A US 3689174DA US 3689174 A US3689174 A US 3689174A
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US
United States
Prior art keywords
vane
holding
blocks
blade ring
combination defined
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
US105551A
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English (en)
Inventor
Thomas J Rahaim
George M Mierley Sr
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.)
Westinghouse Electric Corp
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Westinghouse Electric Corp
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Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
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Publication of US3689174A publication Critical patent/US3689174A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/915—Pump or portion thereof by casting or molding

Definitions

  • ABSTRACT In the manufacturing of stator vanes for the first stage of a multi-stage axial flow gas turbine, casting difiiculty and casting cost are reduced by making a separate casting for each vane instead of making segmental groups of vanes which are costly due to a high casting rejection rate.
  • the vanes are supported by grooved holding blocks attached to the blade ring of the turbine, and they are readily assembled or removed.
  • An improved cooling system is provided for the vanes which are of a hollow construction.
  • This invention relates, generally, to axial flow turbine structures and, more particularly, to stator vane structures for the first stage of a multi-stage axial flow gas turbine.
  • stator vanes for axial flow gas turbines have been cast in segmental groups of, for example, four vanes in each group. This has been difficult and costly due to a high casting rejection rate. Also, the segments have been installed by inserting them in grooves in the blade ring extending transversely of the turbine axis. This made removal and replacement of a segmental group difficult and time consuming.
  • each stator vane structure for the first stage of a multi-stage axial flow gas turbine is made a separate casting.
  • the vane structures are supported by axially grooved holding blocks attached to the blade ring of the turbine.
  • Axially spaced holding lugs on each vane structure slide axially of the turbine in grooves in two adjacent blocks.
  • each vane structure can be removed and replaced separately from the other vane structures.
  • the vanes are of a hollow construction, and cooling air is admitted into each vane through an opening in each holding block into a separate air chamber for each vane, so that failure of any one vane will not rob its neighbors of their air supply.
  • FIG. 1 is a view, partly in elevation and partly in axial section, of a portion of a gas turbine incorporating the invention
  • FIG. 2 is a view, in plan, of one of the holding blocks utilized in the structure shown in FIG. 1;
  • FIG. 3 is a projected side elevation, of a portion of DESCRIPTION OF THE PREFERRED EMBODIMENT
  • the structure shown therein comprises a portion of the first stage of an axial flow gas turbine 10 which includes an annular array of separate first stage stator vane structures 12 (only one shown) and an annular row of first stage rotor blades 14 (only one shown) disposed immediately downstream from the stationary vanes 12.
  • the rotor blades 14 are suitably attached to the periphery of a rotor disc 15, only a portion of which is shown, secured to ,a shaft (not shown) rotatably mounted in the turbine casing in a manner well known in the art.
  • the turbine 10 may include additional expansion stages comprising stationary vanes and rotary blades disposed downstream from the blades 14, thereby providing a multi-stage turbine.
  • a hot motive gas is supplied to the turbine from suitable combustion chambers (not shown).
  • the hot motive gas flows from the combustion chambers through the stationary vanes and the rotating blades, thereby driving the turbine shaft by energy extracted from the hot motive fluid, in a manner well known in the art.
  • stator vane structures 12 are mounted in a stator blade ring 16 which may be of a fabricated construction comprising a plurality of annular sections 18 of different diameters welded together.
  • the blade ring 16 is disposed inside a turbine casing (not shown) which is generally circular in cross section.
  • a cover 20 may be attached to the blade ring 16 in a suitable manner.
  • arcuate ring segments 22 are mounted in a T-shaped groove 24 in the inner periphery of a section 18 of the blade ring 16 around the rotor blades 14 to reduce leakage of the motive fluid past the rotor blades durin operation of the turbine.
  • stator vanes have been cast in segmental groups of vanes with a certain number of vanes, for example four, secured between an arcuate outer shroud segment and an inner arcuate shroud segment.
  • the outer shroud segments have been mounted in a groove in the blade ring in a manner similar to the ring segments 22.
  • the prior method of casting the vanes in groups has been difficult and costly due to a high casting rejection rate.
  • each vane structure 12 for the first stage of the turbine is cast separately with a vane portion 26 secured between an outer shroud portion 28 and an inner shroud portion 30, thereby simplifying the casting procedure.
  • the outer shroud portions 28 are supported in holding blocks 32 attached to the blade ring 16 by means of screws 34 extending through the blade ring and threaded into holes 36 in each block 32. Additional positioning means for each holding block may be provided by a pin 38 inserted through a flange 40 on the blade ring 16 into one end of each block 32.
  • each holding block 32 is generally parallelogram shaped with an inwardly extending projection 42 on one side of the block.
  • the projection 42 has axially extending grooves 44 and 46 therein for receiving holding lugs 48 on the outer shroud 28 of the vane structure 12, see FIG. 7.
  • Each block has a slight curvature corresponding to the curvature of the blade ring.
  • the blocks 32 may be made by cutting a ring having a generally rectangular cross section with an outside diameter substantially equal to the inside diameter of the first section 18 of the blade ring 16 into a predetermined number of pieces, for example 40. Thus, each block, extends through an arc of 9.
  • the grooves 44 and 46 are machined in each block.
  • the holes 36 are drilled and tapped in each block.
  • An opening 50 is drilled through each block for admitting cooling air into each vane 26 which is of a hollow construction.
  • each block 32 is attached to the blade ring 16 by means of two screws 34 threaded into the holes 36.
  • An advantage of the present structure is thatby providing the vane retaining grooves in separate high strength blocks, the blade ring proper may be made of a less expensive material. Also, since the holding blocks are separate from the blade ring, they may be machined on relatively small machine tools which have a lower cost rate than larger tools required for machining the relatively large blade ring.
  • each vane structure 12 comprises the vane portion 26,which is of a hollow construction, secured between the outer shroud portion 28.
  • Two transversely spaced rows of holding lugs 48 are formed integrally with the outer shroud portion 28.
  • the lugs 48 in each row are spaced axially of the turbine toprovide gaps 49 between lugs, thereby reducing conductive heat transfer from the vane to the holding blocks and the blade ring.
  • a cover member 54 is secured on the outer shroud portion 28, as by brazing, between the two rows of holding lugs 48 to provide a separate air chamber for each vane structure. Cooling air is admitted from the space between the blade ring 16 and the cover 20 through an opening (not shown) in the blade ring, the opening 50 in the holding block 32, an opening 56 in the cover member 54, and into the interior of the vane 26 through an opening 58 in the outer shroud 28. the air is exhausted from the vane through openings 60 in the downstream edge of the vane.
  • the cooling air may be supplied I by a compressor (not shown) or other suitable source and admitted into the space inside the blade ring cover 20' through an opening 62 in the cover 20, see FIG. 1.
  • a compressor not shown
  • Separate cooling air chambers permit separate metering of air to each chamber so that failure of any one vane will not rob its neighbors of their air supply.
  • the fit between the holding block 32 and a flange 64 around the opening 56 in the cover 54 may be made such that a gap is provided to permit compressed air to escape to cool the ambient air surrounding the outside of the cooling chamber.
  • the holding lugs 48 on a vane structure 12 are slid axially of the turbine in the grooves 44 and 46 in two adjacent holding blocks 32 to install the vane structure in the turbine.
  • downstream movement of the vane structure is limited by a spacing member 66 secured to the blade ring 16.
  • a portion 68 on each shroud 28 overlaps a portion 70 on an adjacent shroud see FIG. 7. Upstream movement of the vane structure during operation of the turbine is prevented by the pressure of the motivating fluid. This manner of supporting the separate vane structures in the turbine permits easy removal for inspection and/or replacement of any vane structure without removal of the turbine blade ring cover.
  • the invention provides a turbine stator vane structure and supporting means for the vane structure which have numerous advantages over prior structures.
  • the structures herein disclosed are particularly suitable for use in the first stage of a multi-stage axial flow gas turbine.
  • each vane structure includes holding means slidably disposed in said grooves.
  • the holding means comprises two transversely spaced rows of lugs, each of said rows including a plurality of mutually spaced lugs. 4.
  • the lugs in each row are spaced from each other in axial direction.
  • the vanes are of a hollow construction, and each holding block has an opening therethrough admitting coiling air into a single vane. 6.
  • the holding lugs for each vane structure are disposed in grooves in mating two oppositely adjacent holding blocks.

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)
US105551A 1971-01-11 1971-01-11 Axial flow turbine structure Expired - Lifetime US3689174A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10555171A 1971-01-11 1971-01-11

Publications (1)

Publication Number Publication Date
US3689174A true US3689174A (en) 1972-09-05

Family

ID=22306463

Family Applications (1)

Application Number Title Priority Date Filing Date
US105551A Expired - Lifetime US3689174A (en) 1971-01-11 1971-01-11 Axial flow turbine structure

Country Status (9)

Country Link
US (1) US3689174A (enrdf_load_stackoverflow)
JP (1) JPS5026683B1 (enrdf_load_stackoverflow)
CA (1) CA930671A (enrdf_load_stackoverflow)
CH (1) CH545909A (enrdf_load_stackoverflow)
DE (1) DE2158578A1 (enrdf_load_stackoverflow)
FR (1) FR2122162A5 (enrdf_load_stackoverflow)
GB (1) GB1317529A (enrdf_load_stackoverflow)
IT (1) IT946371B (enrdf_load_stackoverflow)
NL (1) NL7118033A (enrdf_load_stackoverflow)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841787A (en) * 1973-09-05 1974-10-15 Westinghouse Electric Corp Axial flow turbine structure
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
US5092735A (en) * 1990-07-02 1992-03-03 The United States Of America As Represented By The Secretary Of The Air Force Blade outer air seal cooling system
US6224329B1 (en) 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US20070237629A1 (en) * 2006-04-05 2007-10-11 General Electric Company Gas turbine compressor casing flowpath rings
US20100132376A1 (en) * 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Mid turbine frame for gas turbine engine
CN103562502A (zh) * 2011-05-30 2014-02-05 西门子公司 活塞密封环
US20140234073A1 (en) * 2011-04-28 2014-08-21 Kevin Moreton Casing cooling duct
US20170356298A1 (en) * 2016-06-08 2017-12-14 Rolls-Royce Plc Stator vane
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE410331B (sv) * 1976-09-24 1979-10-08 Kronogard Sven Olof Statorkonstruktion avsedd att placeras nedstroms en separat arbetsturbinrotor
GB2115883B (en) * 1982-02-26 1986-04-30 Gen Electric Turbomachine airfoil mounting assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
US2863634A (en) * 1954-12-16 1958-12-09 Napier & Son Ltd Shroud ring construction for turbines and compressors
US3362681A (en) * 1966-08-24 1968-01-09 Gen Electric Turbine cooling

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
US2863634A (en) * 1954-12-16 1958-12-09 Napier & Son Ltd Shroud ring construction for turbines and compressors
US3362681A (en) * 1966-08-24 1968-01-09 Gen Electric Turbine cooling

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841787A (en) * 1973-09-05 1974-10-15 Westinghouse Electric Corp Axial flow turbine structure
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
US5092735A (en) * 1990-07-02 1992-03-03 The United States Of America As Represented By The Secretary Of The Air Force Blade outer air seal cooling system
US6224329B1 (en) 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US20070237629A1 (en) * 2006-04-05 2007-10-11 General Electric Company Gas turbine compressor casing flowpath rings
US20100132376A1 (en) * 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Mid turbine frame for gas turbine engine
US8091371B2 (en) * 2008-11-28 2012-01-10 Pratt & Whitney Canada Corp. Mid turbine frame for gas turbine engine
US20140234073A1 (en) * 2011-04-28 2014-08-21 Kevin Moreton Casing cooling duct
US9759092B2 (en) * 2011-04-28 2017-09-12 Siemens Aktiengesellschaft Casing cooling duct
CN103562502A (zh) * 2011-05-30 2014-02-05 西门子公司 活塞密封环
CN103562502B (zh) * 2011-05-30 2015-11-25 西门子公司 活塞密封环
US9422823B2 (en) 2011-05-30 2016-08-23 Siemens Aktiengesellschaft Piston seal ring
US20170356298A1 (en) * 2016-06-08 2017-12-14 Rolls-Royce Plc Stator vane
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling

Also Published As

Publication number Publication date
FR2122162A5 (enrdf_load_stackoverflow) 1972-08-25
JPS5026683B1 (enrdf_load_stackoverflow) 1975-09-02
GB1317529A (en) 1973-05-23
NL7118033A (enrdf_load_stackoverflow) 1972-07-13
DE2158578A1 (de) 1972-07-27
IT946371B (it) 1973-05-21
CA930671A (en) 1973-07-24
CH545909A (enrdf_load_stackoverflow) 1974-02-15

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