US2609176A - Turbine nozzle guide vane construction - Google Patents

Turbine nozzle guide vane construction Download PDF

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Publication number
US2609176A
US2609176A US139867A US13986750A US2609176A US 2609176 A US2609176 A US 2609176A US 139867 A US139867 A US 139867A US 13986750 A US13986750 A US 13986750A US 2609176 A US2609176 A US 2609176A
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US
United States
Prior art keywords
vanes
guide
turbine
guide vane
turbine nozzle
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
US139867A
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English (en)
Inventor
Purvis Joseph Thompson
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.)
AV Roe Canada Ltd
Original Assignee
AV Roe Canada Ltd
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 AV Roe Canada Ltd filed Critical AV Roe Canada Ltd
Priority to US139867A priority Critical patent/US2609176A/en
Priority to GB1192/51A priority patent/GB689216A/en
Priority to FR1031214D priority patent/FR1031214A/fr
Priority to CH294451D priority patent/CH294451A/fr
Priority to DEC3698A priority patent/DE843700C/de
Application granted granted Critical
Publication of US2609176A publication Critical patent/US2609176A/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
    • 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 turbines and other axial flow power conversion machines wherein the blading is subjected to a flow of'fluid at relatively high temperatures.
  • the invention more specifi- 3 Claims. (01. 253-78) 2 7 guide vane mounting that permits the ready removal and replacement of worn or damaged parts.
  • a still further object of the invention is to provide a guide vane mounting arrangement concally relates to an improved mounting for tursisting of the smallest possible number of parts.
  • bine nozzle guide vanes Other objects and advantages will become ap- It is customary, in the mounting of turbine parent during the course of the following descripnozzle guide vanes for axial flow turbines, to setion. ,cure the said vanes by their inner platforms or
  • Fig. 1 is a fragvanes to the surrounding engine casing.
  • FIG. 2 is a fragmentary sectional replace individual guide vanes which may become view taken on a radial plane through t e casing burnt or otherwise damagedin service.
  • Suitable means are provided to hold the casing
  • the principal object of this invention i t proand the inner structure in spaced relationship. vide a mounting for turbine nozzle guide vanes he Words inner and outer are used herein which will enable the position of the vane nde in reference to the senses radial to the engine). operating conditions tobe predetermined with According to the invention, each of a plurality some accuracy and at the same time W111 facilitate of o le uid v s 12 t ds radially cr the replacement of vanes which become damaged an annular p c d b tween the fiXed in service. inner structure II and the fixed outer casing 10.
  • a circumferential channel [4 is provided in the a mounting for turbine nozzle guide vanes which inner structure II, the sides of the said channel provides firm support against the loads imposed being d fi d y an a ul r flan e I5 on the inner by the working fluid and makes provision fo structure H and a flanged retaining ring l6 atrelative mov ment b tw th blading and t tached thereto.
  • pr vi d a circumferentions.
  • Another object of the invention is to provide e 011118! Casing and a turbine r d rin a mounting that permits each guide vane to'exsecured to the 0111591 n pand or contract independently in relation to the Each guide v n has an ou r base member or adjoining guide vanes, platform [9 and an inner base member or plat-
  • Another object of the invention is to provide form i" which provide means for'mounfing the a guide vane mounting wherein the-loads imvanes m the channels the vanes posed by the Working fluid tend to hold the guide l 2 curve away from the axial direction at a convanes firmly against their mountings thereby slderable aligle and adJacent vanes must b I v spaced relatively closely together, the inner and helping to support the guide vanes and mimmiz- Outer vane platforms 2n and '9 r k d th t ing the leakage of working fluid through the in
  • Another object of the invention is to provide a ltwhe'i'nnei' tpl tfd 2' chfd thm vanes I2 has an inwardly projecting flange 2I at the forward edge of the platform and a smaller inwardly projecting flange 22 at the rear edge of the platform.
  • the flange 2I is provided with a radial slot 23 which engages with one of a series of evenly spaced rearwardly projecting teeth 24 carried by'ithe flangeIS on thein'n'er structure I I.
  • each-of the guide 'vanes I2 is located in channel I'I and'has a rela- 'tively small outwardly projecting flange 2-5 at.
  • the right-angled flange 26 is provided witha:radial slot--21 engaging with oneof a series of evenly spaced forwardly-projecting teeth-28 on-the-forward-face of turbine shroud-ring I8.
  • ii-clamping plate "29 is removably attached to-the shroudring .IB and has an annular shoulder '29 at the inward end, which receives the outermost edge of the-right-angled flange 26 oneach-of .theouter platforms I 9 andclamps thesaid flanges inpositionagainstshroud ring I'8.
  • Thesmallei flange on-the outer-platformIQ is just long enough radially to rest against the rear face Ill of the outercasing 'I-Il when the guide-vanes I2 are'in extreme contracted positionrelative tothe inner structure. I I and the outer casing I0.
  • the guide vanes I-2 are fixed with respect to-the outercasing I U by meansrofthe clamping; plate 2 9 andtheiengagement of teeth 28 with the slots 21, whilethe-vanes are'free to 'expand and contract relativetothe innerstructure II because relative radialmovement is possible between the teeth -24 and the slots'23.
  • the axial-gas loads acting on the vanes are earned by the forward reaction of the 1 turbine shroud ring I8 against the read edges of the right-angled flanges 26" at therear-of outer platforms I9-and by the forwardreaction ofthe retaining ring l6 against theflanges-22 atthe rear of innerplatforms '20.
  • Th-etangential-gas loads are carried by thetangential reactions of -teeth Hand-28, againstthe-sides of the radial-slots 23 and- 2'! respectively.
  • the guide vanesarei positively located with 'respect to the shroud ring I8 and the outer casing I0; and are independent of-the radial expans-ion andcontraction of zth'e inner structure I I.
  • the -operating temperatures of the shroud ring and the outer easing are 'well understood and can -be easily-controlled by insulation and other means so that the-position of thesguide vanes under operating :conditionscan Ebe raccurately-predetermined; this is a point of some importance since the relationship betweenthe guide vanes and thei turbirre' rotor blades has amarked effect-upon theperformanee of-the engine.
  • Thermal insulating material may be placed in the channels I4 and H, in order to prevent excessive loss'ofhea't fromthejguideivanes and also to prevent the damage to other which escaping heat might cause.
  • each of theguidevanes having an -outer platform adjacent the outer casing and an inner platform adjacent the inner structure, I m-cans on theouter casing 'securing the outer platforms to the outer cas-ing,--'-each oftheguide vane inner platforms -having atits upstrear'n side radially 'inwardiy extending projection, ithe projectiohs being 11in fradially rand axially slidable engagement 'with thei-tee'th to; permit": radial and.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US139867A 1950-01-21 1950-01-21 Turbine nozzle guide vane construction Expired - Lifetime US2609176A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US139867A US2609176A (en) 1950-01-21 1950-01-21 Turbine nozzle guide vane construction
GB1192/51A GB689216A (en) 1950-01-21 1951-01-16 Turbine nozzle guide vane construction
FR1031214D FR1031214A (fr) 1950-01-21 1951-01-19 Aube directrice pour tuyère de turbine
CH294451D CH294451A (fr) 1950-01-21 1951-01-20 Couronne d'aubes directrices pour turbine à écoulement axial.
DEC3698A DE843700C (de) 1950-01-21 1951-01-21 Lagerung fuer die Duesenleitschaufeln von Turbinen

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US139867A US2609176A (en) 1950-01-21 1950-01-21 Turbine nozzle guide vane construction

Publications (1)

Publication Number Publication Date
US2609176A true US2609176A (en) 1952-09-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US139867A Expired - Lifetime US2609176A (en) 1950-01-21 1950-01-21 Turbine nozzle guide vane construction

Country Status (5)

Country Link
US (1) US2609176A (fr)
CH (1) CH294451A (fr)
DE (1) DE843700C (fr)
FR (1) FR1031214A (fr)
GB (1) GB689216A (fr)

Cited By (16)

* 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
US2771622A (en) * 1952-05-09 1956-11-27 Westinghouse Electric Corp Diaphragm apparatus
US2808226A (en) * 1952-02-08 1957-10-01 Ryan Aeronautical Co Turbine nozzle box
US3300180A (en) * 1964-11-17 1967-01-24 Worthington Corp Segmented diaphragm assembly
US3867063A (en) * 1972-10-14 1975-02-18 Eduard Grigorievich Bulavin Stator of multistage turbomachine
US4470754A (en) * 1980-05-19 1984-09-11 Avco Corporation Partially segmented supporting and sealing structure for a guide vane array of a gas turbine engine
US4552509A (en) * 1980-01-31 1985-11-12 Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for joining two relatively rotatable turbomachine components
US4725199A (en) * 1985-12-23 1988-02-16 United Technologies Corporation Snap ring construction
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
FR2660362A1 (fr) * 1990-04-03 1991-10-04 Gen Electric Structure de fixation des extremites exterieures des aubes d'une turbine.
FR2681902A1 (fr) * 1991-09-27 1993-04-02 Gen Electric Agencements de montage pour tuyeres de turbine.
US6641144B2 (en) * 2001-12-28 2003-11-04 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
US8984859B2 (en) 2010-12-28 2015-03-24 Rolls-Royce North American Technologies, Inc. Gas turbine engine and reheat system
US20160177835A1 (en) * 2014-12-22 2016-06-23 Pratt & Whitney Canada Corp. Gas turbine engine with angularly offset turbine vanes
US10072516B2 (en) 2014-09-24 2018-09-11 United Technologies Corporation Clamped vane arc segment having load-transmitting features

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2915280A (en) * 1957-04-18 1959-12-01 Gen Electric Nozzle and seal assembly
NL104794C (fr) * 1957-08-16
DE1246321B (de) * 1964-10-02 1967-08-03 Daimler Benz Ag Leitschaufelkranz fuer axial durchstroemte Turbinen oder Verdichter von Gasturbinentriebwerken
FR1339521A (fr) * 1966-06-10 1963-10-11 Rolls Royce Machine à circulation de fluide
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
GB2268978B (en) * 1992-07-21 1995-11-08 Rolls Royce Plc Fan for a ducted fan gas turbine engine
DE10223655B3 (de) 2002-05-28 2004-02-12 Mtu Aero Engines Gmbh Anordnung zum axialen und radialen Fixieren der Leitschaufeln eines Leitschaufelkranzes einer Gasturbine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US973472A (en) * 1908-03-28 1910-10-25 Gen Electric Turbine-nozzle.
US1061675A (en) * 1911-12-18 1913-05-13 Gen Electric Diaphragm and nozzle construction for turbines.
US2013512A (en) * 1933-03-11 1935-09-03 Laval Steam Turbine Co Guide vane and diaphragm construction for turbines
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine
US2488875A (en) * 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
US2488867A (en) * 1946-10-02 1949-11-22 Rolls Royce Nozzle-guide-vane assembly for gas turbine engines
US2494821A (en) * 1946-03-25 1950-01-17 Rolls Royce Means for supporting the nozzles of the combustion chambers of internal-combustion turbines

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US973472A (en) * 1908-03-28 1910-10-25 Gen Electric Turbine-nozzle.
US1061675A (en) * 1911-12-18 1913-05-13 Gen Electric Diaphragm and nozzle construction for turbines.
US2013512A (en) * 1933-03-11 1935-09-03 Laval Steam Turbine Co Guide vane and diaphragm construction for turbines
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine
US2494821A (en) * 1946-03-25 1950-01-17 Rolls Royce Means for supporting the nozzles of the combustion chambers of internal-combustion turbines
US2488867A (en) * 1946-10-02 1949-11-22 Rolls Royce Nozzle-guide-vane assembly for gas turbine engines
US2488875A (en) * 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine

Cited By (16)

* 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
US2808226A (en) * 1952-02-08 1957-10-01 Ryan Aeronautical Co Turbine nozzle box
US2771622A (en) * 1952-05-09 1956-11-27 Westinghouse Electric Corp Diaphragm apparatus
US3300180A (en) * 1964-11-17 1967-01-24 Worthington Corp Segmented diaphragm assembly
US3867063A (en) * 1972-10-14 1975-02-18 Eduard Grigorievich Bulavin Stator of multistage turbomachine
US4552509A (en) * 1980-01-31 1985-11-12 Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for joining two relatively rotatable turbomachine components
US4470754A (en) * 1980-05-19 1984-09-11 Avco Corporation Partially segmented supporting and sealing structure for a guide vane array of a gas turbine engine
US4725199A (en) * 1985-12-23 1988-02-16 United Technologies Corporation Snap ring construction
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
FR2660362A1 (fr) * 1990-04-03 1991-10-04 Gen Electric Structure de fixation des extremites exterieures des aubes d'une turbine.
FR2681902A1 (fr) * 1991-09-27 1993-04-02 Gen Electric Agencements de montage pour tuyeres de turbine.
US6641144B2 (en) * 2001-12-28 2003-11-04 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
US8984859B2 (en) 2010-12-28 2015-03-24 Rolls-Royce North American Technologies, Inc. Gas turbine engine and reheat system
US10072516B2 (en) 2014-09-24 2018-09-11 United Technologies Corporation Clamped vane arc segment having load-transmitting features
US20160177835A1 (en) * 2014-12-22 2016-06-23 Pratt & Whitney Canada Corp. Gas turbine engine with angularly offset turbine vanes

Also Published As

Publication number Publication date
GB689216A (en) 1953-03-25
FR1031214A (fr) 1953-06-22
CH294451A (fr) 1953-11-15
DE843700C (de) 1952-07-10

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