US2625367A - Mounting of the stator blades of gaseous fluid turbines - Google Patents

Mounting of the stator blades of gaseous fluid turbines Download PDF

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Publication number
US2625367A
US2625367A US172822A US17282250A US2625367A US 2625367 A US2625367 A US 2625367A US 172822 A US172822 A US 172822A US 17282250 A US17282250 A US 17282250A US 2625367 A US2625367 A US 2625367A
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United States
Prior art keywords
ring
blades
stator member
stator
flange
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Expired - Lifetime
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US172822A
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Horace S Rainbow
Paul Donald
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Armstrong Siddeley Motors Ltd
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Armstrong Siddeley Motors Ltd
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    • 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

  • This invention relates to the mounting of the stator blades of a gaseous fluid turbine, and particularly in the case when the stator blades are hollow and adapted to be internally cooled by air flowing therethrough-as described, for example, in the specification of co -pending application No. 172,821, in the name of Horace Sinclair Rainbow and Donald Paul, filed concurrently herewith.
  • Figure l is a fragmentary section of a gas turbine showing one of the stator blades of the first row arranged according to the invention.
  • Figure 2 is a perspective view of the mounting for the radially-outer end. thereof.
  • each hollow blade l2 extends slidingly through a correspondingly-shaped hole in a ring I3 which is welded or otherwise secured to the outwardly-directed flanges l4, I5 of a co-axial inner ring it providing, with the outer ring, an inner annular chamber 11 to receive cooling air which has passed radially inwardly of the blade, and direct it rearwardly, through holes It provided for the purpose on to the roots I9 of the first row of rotor blades 20.
  • This inner ring 46 preferably has radially-inwardly directed teeth 2! for sliding engagement with teeth of a structural member 22.
  • the inner ring v26 is mounted in counter-bored grooves 35, 36 provided, at the forward edge of the ring 26, in .a flanged ring 31 which is bolted at 38 to the adjacent flange 28 of the stator member 21, and, at its rearward edge, in the first-stage rotor shroud 39 (assuming that the turbine has The rotor shroud 39 has an outward flange All which is bolted at 41 to the adjacent flange 29 of the stator member 21.
  • stator member to be slidaxially 1 blades carrying platforms which. with the platforms of adjacent blades, form a continuous cylindrical ring adjacent said stator member, and an inner ring having holes slidably to receive and locate said blades, said cylindrical ring being disposed sandwich-fashion between said inner 3 ring and said stator member so that,'on axial removal of said stator member, any of said blades and its associated platform can be separately withdrawn in the radially outward direction.
  • a stator of a gaseous fluid axial-flow turbine, comprising an annular stator member formed with outwardly-directed channel flanges between which is constituted an annular chamher, a row of hollow blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blades extending through and carrying platform which, with the platforms of adjacent blades, form a continuous cylindrical inwardly-directed flange adjacent the other axial side, an internal annular stator member with outwardly-directed flanges, a shroud ring having an outwardly-directed flange, said shroud ring flange bolted up to one of the flanges of said stator member and having a toothed engagement with said inwardly-directed flange of said external ring allowing of relative axial movement thereof, said stator member jointly providing with said external ring an annular space, open ring adjacent said stator member, and an inner 3.
  • a stator of a gaseous fluid axial-flow turbine, comprising an annular stator member formed with outwardly-directed channel flanges, a row of blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blade carrying platforms which, with the platforms of adjacent blades, form a continuous cylindrical ring adjacent said stator member, an inner ring having holes slidably to receive and locate said blades, said inner ring clamping the platform ring sandwich-fashion against said stator member so that, on removal of said stator member, any of said blades and its associated platform can be separately withdrawn in the radially outward direction, a flanged ring bolted to one of said channel flanges, and a shroud ring boltedto the other of said channel flanges, said flanged ring and said shroud ring both being counter-bored to receive and locate the edges of said inner ring.
  • a stator of a gaseous fluid axial-flow turbine, comprising an annular stator member, a row of blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blades carrying platforms which, with the platforms of adjacent blades, form a continudus cylindrical ring adjacent said stator member, an

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

Description

Jan. 13, 1953 H. s. RAINBOW ETAL MOUNTING OF THE STATOR BLADES OF GASEOUS FLUID TURBINES Filed July 10, 1950 2 SHEETS-SHEET 2 ih'lventors H J. emvaa/v 00AM! .0 94M.
Patented Jan. 13, 1953 UNITED STATES PATENT OFFICE MOUNTING OF THE STATOR BLADES OF GASEOUS FLUID TURBINES Application July 10, 1950, Serial No. 172,822 In Great Britain August 27, 1949 6 Claims. 1
. This invention relates to the mounting of the stator blades of a gaseous fluid turbine, and particularly in the case when the stator blades are hollow and adapted to be internally cooled by air flowing therethrough-as described, for example, in the specification of co -pending application No. 172,821, in the name of Horace Sinclair Rainbow and Donald Paul, filed concurrently herewith.
According to the invention, each stator blade of a row is supported at its radially inner end for radial outward withdrawal, being located in other directions at that end, and fast with its outer end is a platform which is clamped sandwich-fashion between stationary inner and outer co-axial rings providing location for the platform in all directions. Thus, in order to remove a blade the stationary outer ring must be'removed, whereupon any blade of that row can be withdrawn radially outwardly and replaced by a new blade when that is desired.
In the accompanying drawings Figure l is a fragmentary section of a gas turbine showing one of the stator blades of the first row arranged according to the invention; and
Figure 2 is a perspective view of the mounting for the radially-outer end. thereof.
In one construction according to the invention, as applied to the first stator blade row of a gas turbine the blades of which are arranged as disclosed in the specification aforesaid, the radiallyinner end ll of each hollow blade l2 extends slidingly through a correspondingly-shaped hole in a ring I3 which is welded or otherwise secured to the outwardly-directed flanges l4, I5 of a co-axial inner ring it providing, with the outer ring, an inner annular chamber 11 to receive cooling air which has passed radially inwardly of the blade, and direct it rearwardly, through holes It provided for the purpose on to the roots I9 of the first row of rotor blades 20. This inner ring 46 preferably has radially-inwardly directed teeth 2! for sliding engagement with teeth of a structural member 22.
The outer end 24 of the blade carries a platform 25 which is rhomboidal in plan view but part-cylindrical about the axis of the turbine and of such size as to form with the platforms of the rest of the blades (when assembled to provide the row) a continuous ring surface. This continuous ring surface is clamped, sandwich-fashion, between an inner ring 25 (having shaped holes to receive the outer ends of the blades) and an outer stator member 21 formed with outwardly di- 'rected channel flanges 28. 29 between which is more than one stage) The inner ring v26 is mounted in counter-bored grooves 35, 36 provided, at the forward edge of the ring 26, in .a flanged ring 31 which is bolted at 38 to the adjacent flange 28 of the stator member 21, and, at its rearward edge, in the first-stage rotor shroud 39 (assuming that the turbine has The rotor shroud 39 has an outward flange All which is bolted at 41 to the adjacent flange 29 of the stator member 21.
The exhaust cone assembly 43 is supported by an external channel-sectionring 44 forming the outer wall 45 of the outer annular chamber 30,, this external ring having an internal radial toothed engagement 45 with teeth '41 on the periphery of the flange 4'!) of the first stage rotor shroud It also has a flange 48 at its forward end which is bolted up, at 49, to the rearward end of the outer casing of the duct 32 with an interposed abutment ring 59. The latter has at least one axially-projecting 'tang 5|, within the interior of the outer annular chamber 38, which, when the parts are secured in position, nips the rearward flange 2B of the stator member 21 against the teeth 45 of the external ring 44 and against the flange 4'!) of' the first stage rotor shroud 39.
To dismantle the apparatus, the bolts 49 holding the external ring M. (which supports the exhaust cone assembly) are first removed and these parts then slid rearwardly, the toothed engagement 4%, 41 with the flange of the first stage rotor shroud 39 allowing of this. This discloses the mounting bolt. indicated at 53, for the second stage rotor shroud which, and the second stage stator 54, can then be removed. The abutment ring 53 can then be moved angularly in order to bring its tang 5| into alignment with a slot 55, provided for the purpose, in the flange 29 "of the stator member 27, whereupon the abutment ring can he slid axially rearwardly. This "provides access to the bolts 3-?! securing the forward flange 28 of the stator member to the flanged ring 37,
. thus enabling the stator member to be slidaxially 1 blades carrying platforms which. with the platforms of adjacent blades, form a continuous cylindrical ring adjacent said stator member, and an inner ring having holes slidably to receive and locate said blades, said cylindrical ring being disposed sandwich-fashion between said inner 3 ring and said stator member so that,'on axial removal of said stator member, any of said blades and its associated platform can be separately withdrawn in the radially outward direction.
2. A stator, of a gaseous fluid axial-flow turbine, comprising an annular stator member formed with outwardly-directed channel flanges between which is constituted an annular chamher, a row of hollow blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blades extending through and carrying platform which, with the platforms of adjacent blades, form a continuous cylindrical inwardly-directed flange adjacent the other axial side, an internal annular stator member with outwardly-directed flanges, a shroud ring having an outwardly-directed flange, said shroud ring flange bolted up to one of the flanges of said stator member and having a toothed engagement with said inwardly-directed flange of said external ring allowing of relative axial movement thereof, said stator member jointly providing with said external ring an annular space, open ring adjacent said stator member, and an inner 3. A stator, of a gaseous fluid axial-flow turbine, comprising an annular stator member formed with outwardly-directed channel flanges, a row of blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blade carrying platforms which, with the platforms of adjacent blades, form a continuous cylindrical ring adjacent said stator member, an inner ring having holes slidably to receive and locate said blades, said inner ring clamping the platform ring sandwich-fashion against said stator member so that, on removal of said stator member, any of said blades and its associated platform can be separately withdrawn in the radially outward direction, a flanged ring bolted to one of said channel flanges, and a shroud ring boltedto the other of said channel flanges, said flanged ring and said shroud ring both being counter-bored to receive and locate the edges of said inner ring.
4. A-stator, of a gaseous fluid axial-flow turbine, comprising an annular stator member formed with outwardly-directed channel flanges, a row of blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of aid blades carrying platforms which, with the platforms of adjacent blades, form a continuous cylindrical ring adjacent said stator member, an inner ring having holes slidably to receive and locate said blades, said inner ring clamping the platform ring sandwich-fashion against said stator member so that, on removal of said stator member, any of said blades and its associated at the axial side remote from said shroud ring, to receive cooling air, an abutment rin bolted up to the outwardly extending flange of said external ring, said abutment ring having at least one tang extending across said annular chamber to hold the said one flange of said stator member against the flange of said shroud ring and against the internal flange of said external ring, the said one flange of said stator member having a slot in it to receive said tang when said abutment ring is turned angularly with respect to said stator member, a flanged ring bolted to the other flange of said stator member, a row of hollow blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blades carrying platforms which, with the platforms of adjacent blades, form a continuous cylindrical ring adjacent said stator member, said stator member having holes in it to place said annular space in communication with the open outer ends of said blades, and an inner ring having holes slidably to receive and locate the outer ends of said blades, said inner ring I clamping said cylindrical ring sandwich-fashion against said stator member.
6. A stator, of a gaseous fluid axial-flow turbine, comprising an annular stator member, a row of blades, means supporting the inner ends of said blades against movement in all directions but the radial one, the outer extremities of said blades carrying platforms which, with the platforms of adjacent blades, form a continudus cylindrical ring adjacent said stator member, an
= inner ring having holes to slidably receive and locate said blades, said platform ring'being disposed sandwich-fashion between 'said stator member and said inner ring so that, on removal of said stator member, any of said blades and 1 it associated platform can be separately with- REFERENCES CITED The following references are of record inthe file of this patent:
UNITED STATES PATENTS Number Name Date 2,402,418 Kroon June 18, 1946 2,417,486 Hagemann et al. Mar. 18, 1947 2,427,244 Warner Sept. 9, 1947 OTHER REFERENCES Publication entitled Flight, vol. Lvn,
issue 2158, page 544, dated May 4, 1950.
US172822A 1949-08-27 1950-07-10 Mounting of the stator blades of gaseous fluid turbines Expired - Lifetime US2625367A (en)

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GB289171X 1949-08-27

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CH (1) CH289171A (en)
DE (1) DE823823C (en)
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GB (1) GB666537A (en)

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2702688A (en) * 1951-12-26 1955-02-22 Gen Electric Gas turbine nozzle casing
US2738949A (en) * 1950-06-29 1956-03-20 Rolls Royce Gas-turbine engines and nozzle-guide-vane assemblies therefor
US2793832A (en) * 1952-04-30 1957-05-28 Gen Motors Corp Means for cooling stator vane assemblies
US2801075A (en) * 1952-12-22 1957-07-30 Gen Motors Corp Turbine nozzle
US2803428A (en) * 1952-07-21 1957-08-20 William R Garnett Method and means for minimizing cavitation and pitting in hydraulic turbines
US2808226A (en) * 1952-02-08 1957-10-01 Ryan Aeronautical Co Turbine nozzle box
US2840298A (en) * 1954-08-09 1958-06-24 Gen Motors Corp Heated compressor vane
US2859934A (en) * 1953-07-29 1958-11-11 Havilland Engine Co Ltd Gas turbines
DE1055884B (en) * 1954-03-02 1959-04-23 Bristol Aero Engines Ltd Flame tube for a combustion chamber of a gas turbine engine
US2932485A (en) * 1954-10-01 1960-04-12 United Aircraft Corp Stator construction
US2942844A (en) * 1952-12-22 1960-06-28 Gen Motors Corp Turbine nozzle
US2956772A (en) * 1955-08-19 1960-10-18 John C Freche Liquid-spray cooling method
US3071346A (en) * 1960-06-21 1963-01-01 Wilgus S Broffitt Turbine nozzle
US3288434A (en) * 1964-08-20 1966-11-29 Bbc Brown Boveri & Cie Gas turbine adapted for partial activation
US3341114A (en) * 1966-03-04 1967-09-12 Gen Electric Anti-icing means
US3363416A (en) * 1965-09-21 1968-01-16 Bristol Siddeley Engines Ltd Gas turbine engines
US3365125A (en) * 1966-08-03 1968-01-23 Gen Motors Corp Turbomachinery
US3529903A (en) * 1968-11-29 1970-09-22 Westinghouse Electric Corp Nozzle blade structure
US3529906A (en) * 1968-10-30 1970-09-22 Westinghouse Electric Corp Static seal structure
US3544231A (en) * 1968-03-22 1970-12-01 Sulzer Ag Stator-blade assembly for turbomachines
US3581569A (en) * 1969-11-28 1971-06-01 Avco Corp Mounting of fluidic temperature sensor in gas turbine engines
US4384822A (en) * 1980-01-31 1983-05-24 Motoren- Und Turbinen-Union Munchen Gmbh Turbine nozzle vane suspension for gas turbine engines
US4585390A (en) * 1984-06-04 1986-04-29 General Electric Company Vane retaining means
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
US4962640A (en) * 1989-02-06 1990-10-16 Westinghouse Electric Corp. Apparatus and method for cooling a gas turbine vane
US5441385A (en) * 1993-12-13 1995-08-15 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
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
US6302648B1 (en) * 1998-06-01 2001-10-16 Mitsubishi Heavy Industries, Ltd. Steam turbine jointed stationary blade

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB723505A (en) * 1952-11-18 1955-02-09 Parsons & Marine Eng Turbine Improvements in or relating to turbine nozzles
BE529252A (en) * 1953-06-01
US3088281A (en) * 1956-04-03 1963-05-07 Bristol Siddeley Engines Ltd Combustion chambers for use with swirling combustion supporting medium
US3075744A (en) * 1960-08-16 1963-01-29 United Aircraft Corp Turbine nozzle vane mounting means
GB1053846A (en) * 1962-10-10
DE1246321B (en) * 1964-10-02 1967-08-03 Daimler Benz Ag Guide vane ring for axially flowed turbines or compressors of gas turbine engines

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2402418A (en) * 1943-01-20 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2417486A (en) * 1943-02-19 1947-03-18 Allis Chalmers Mfg Co Nozzle construction
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2402418A (en) * 1943-01-20 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2417486A (en) * 1943-02-19 1947-03-18 Allis Chalmers Mfg Co Nozzle construction
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2738949A (en) * 1950-06-29 1956-03-20 Rolls Royce Gas-turbine engines and nozzle-guide-vane assemblies therefor
US2702688A (en) * 1951-12-26 1955-02-22 Gen Electric Gas turbine nozzle casing
US2808226A (en) * 1952-02-08 1957-10-01 Ryan Aeronautical Co Turbine nozzle box
US2793832A (en) * 1952-04-30 1957-05-28 Gen Motors Corp Means for cooling stator vane assemblies
US2803428A (en) * 1952-07-21 1957-08-20 William R Garnett Method and means for minimizing cavitation and pitting in hydraulic turbines
US2942844A (en) * 1952-12-22 1960-06-28 Gen Motors Corp Turbine nozzle
US2801075A (en) * 1952-12-22 1957-07-30 Gen Motors Corp Turbine nozzle
US2859934A (en) * 1953-07-29 1958-11-11 Havilland Engine Co Ltd Gas turbines
DE1055884B (en) * 1954-03-02 1959-04-23 Bristol Aero Engines Ltd Flame tube for a combustion chamber of a gas turbine engine
US2840298A (en) * 1954-08-09 1958-06-24 Gen Motors Corp Heated compressor vane
US2932485A (en) * 1954-10-01 1960-04-12 United Aircraft Corp Stator construction
US2956772A (en) * 1955-08-19 1960-10-18 John C Freche Liquid-spray cooling method
US3071346A (en) * 1960-06-21 1963-01-01 Wilgus S Broffitt Turbine nozzle
US3288434A (en) * 1964-08-20 1966-11-29 Bbc Brown Boveri & Cie Gas turbine adapted for partial activation
US3363416A (en) * 1965-09-21 1968-01-16 Bristol Siddeley Engines Ltd Gas turbine engines
US3341114A (en) * 1966-03-04 1967-09-12 Gen Electric Anti-icing means
US3365125A (en) * 1966-08-03 1968-01-23 Gen Motors Corp Turbomachinery
US3544231A (en) * 1968-03-22 1970-12-01 Sulzer Ag Stator-blade assembly for turbomachines
US3529906A (en) * 1968-10-30 1970-09-22 Westinghouse Electric Corp Static seal structure
US3529903A (en) * 1968-11-29 1970-09-22 Westinghouse Electric Corp Nozzle blade structure
US3581569A (en) * 1969-11-28 1971-06-01 Avco Corp Mounting of fluidic temperature sensor in gas turbine engines
US4384822A (en) * 1980-01-31 1983-05-24 Motoren- Und Turbinen-Union Munchen Gmbh Turbine nozzle vane suspension for gas turbine engines
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
US4585390A (en) * 1984-06-04 1986-04-29 General Electric Company Vane retaining means
US4962640A (en) * 1989-02-06 1990-10-16 Westinghouse Electric Corp. Apparatus and method for cooling a gas turbine vane
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
US5441385A (en) * 1993-12-13 1995-08-15 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
US5554001A (en) * 1993-12-13 1996-09-10 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
US5591003A (en) * 1993-12-13 1997-01-07 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
US6302648B1 (en) * 1998-06-01 2001-10-16 Mitsubishi Heavy Industries, Ltd. Steam turbine jointed stationary blade

Also Published As

Publication number Publication date
DE823823C (en) 1951-12-06
CH289171A (en) 1953-02-28
FR1021266A (en) 1953-02-17
GB666537A (en) 1952-02-13

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