US2447942A - Turbine distributor and nozzle - Google Patents

Turbine distributor and nozzle Download PDF

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Publication number
US2447942A
US2447942A US626104A US62610445A US2447942A US 2447942 A US2447942 A US 2447942A US 626104 A US626104 A US 626104A US 62610445 A US62610445 A US 62610445A US 2447942 A US2447942 A US 2447942A
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United States
Prior art keywords
ring
stator
blades
shaped member
expansion
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
US626104A
Inventor
Imbert Roger Jean
Mission Gilbert
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Rateau SA
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Rateau SA
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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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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

  • the present invention covers an arrangement for mounting the stationary bladings of gas turbines or generally speaking of the bladings of any turbo-machines operating with iiuid at high temperatures; according to the invention, the blades are integral only with a single ring-shaped member and they are mounted on the side opposite to said vring-shaped member in a manner such as will allow radial displacement due to their expansion.
  • Fig. 1 is a partial axial cross-section showing the us'ual manner of 'executing stationary distributors
  • Figs. 2 to 5 are corresponding views of diiferent forms of execution improved in accordance with said invention.
  • Fig. 2 is an axial cross-section of a first type of distributor.
  • Fig. 3 is a developed cross-section of the stationary blading of said distributor, the crosssection being executed through a coaxial cylinder.
  • Fig. 4 and 5 are halfcross-sections through shaped members leads-to a compression or to a stretching of the blades.
  • Fig. 2 shows the application'of the invention to a first distributor or injecting nozzles of a turbine operating with gases or with highly superl heated steam; the driving fiuid enters through Ythe torus d and expands between the blades c of the nozzle and drives the receiving wheel e.
  • the blades c of the expansion nozzle are provided with two heels or end pieces f and g and are rigidly secured to the outer ring-shaped member i, by means of rivets i for instance.
  • the outer ring-shaped member l is mounted in .its turn in a manner such as will allow its free expansion inside the body h of the stator by means of a radial system of pins or keys k the number of which is at least equal to three.
  • the duid-tightness of the mounting of the ring-shaped member i inside the stator is provided by the correct machining of the lateral surfaces of said member and of the surfaces of the reess housing it inside the stator h and by the pressure of the driving iluid which applies the ring-shaped member against .the down-stream side surface of its recess.
  • the fluid-tightnessV at the center of the distributor is provided by a free or iioating ring l bearing, under the action of the pressure of the driving gases passing out of the torus, on one hand against the body of the stator h, on the other against the heels g of the blades.
  • a free or iioating ring l bearing under the action of the pressure of the driving gases passing out of the torus, on one hand against the body of the stator h, on the other against the heels g of the blades.
  • the latter are tted inside one another by means of the arrangement shown in Fig. 3, in which the bearing surfaces between adjacent blades are illustrated as forming a series of steps.
  • Figs. 4 and 5 relates more particularly to an intermediary distributor adapted for use either in a gas turbine or in a high pressure steam turbine.
  • Fig. 4 shows more particularly a crosssection through the axis of a blade guiding pin
  • Fig. 5 a cross-section through the pin con- ⁇ heels f1 of the blades which are not mechanically interconnected engage an outer ring shaped member i1 inside which they are centered by a certain number of pins o the number of which is equal at the utmost to that of the blades.
  • a single pin or key may be provided for a group of two or three' consecutive blades.
  • the outer ring-shaped member il is mounted in its turn in a manner such as will allow its free expansion with reference to the stator h of the machine so that the reactions of the stator are prevented from deforming the pin carrying ring-shaped member.
  • the ringshaped member i1 may be guided with reference to the stator by means of radial pins or keys p.
  • a stationary distributor comprising two coaxial rings, a system of blades arranged between said rings, se-
  • a stationary distributor comprising two coaxial-rings, a system of blades arranged between said rings, secured rigidly to only one thereof, and engaging the other ring in a manner allowing the free expansion of the blades with reference thereto, a
  • stator enclosing the two ring-shaped members, the ring-shaped member 1 rigid with the blades being machined along its lateral surface engaging the stator for providing vuid-tightness under the laction of fluid pressure and allowing the free relative expansion of the ring-shaped member with reference to the stator and a system of at least three radial pins rigid with the stator ⁇ and engaging freely the ring-shaped member rigid with the blades for centering said member.
  • a turbo-machineA adaptedv to operate at high temperatures.
  • a stationary distributor including a stator, a ringfitted therein, a system of radial blades rigidly secured to said ring and a lsecond floating ring, adapted to bear under the action of gas pressure both against the periphery of the blades opposed to the periphery engaging the first ring and against the stator.
  • an intermediary distributor including a central ring-shaped member, a system oi radial blades rigidly con- Y manner such as will allow its freev expansion with reference thereto, and radial pins rigid with the stator and freely engaging the outer ring-shaped member for centering same.
  • a turbo-machine adapted to operate at high temperatures and having a stator and at least one wheel rotatablyl mounted in said stator, the provision of a stationary distributor cooperating with said wheel and comprising an external and an internal ring coaxially disposed with reference to said wheel, the said external ring being mounted in a circular groove of said stator with a peripheral play allowing the radial expansion of said ring, guiding means radially disposed in said stator for centering said ring in said stator with respect to said wheel and for ensuring the radial expansion of said ring in said play, a system of blades arranged between said internal and said external ring, means for securing rigidly said blades to only one of said rings, and means providing a radial fitting with a peripheral play between said blades and said other ring, said fitting comprising, on said ring and on the blades, planes at right angles with 'the axis of said wheel and adapted to be applied Vating with said wheel and comprising an external and an internal ring

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

Description

Aug. 24,- Y1948". R. J. trum-:rfr'l-lfAl.l 2,447,942
'leumamsy DISTRIBUTOR AND NozzLE Filed Nov. 1, 1945 Y ,A 2 sheets-sheet 2 n y, ,ff
'rUnBINE DISTRIBUTOR AND Nozzu: anger Jenn Imbert, Paris, and Gilbert Masten.
eux, France, a
(Socit Anonyme), Paris, France,
o! France ors to Socit Bateau a company Application November 1, 1945, Serial No. 626,104 In France December 5, 1944 7 Claims. (Cl. 253-78) The development .of thermic machines operating at high temperatures and chieiiy of gas turbines presents considerable difficulties by reason of the variations in the distribution of the temperature both in space and in time as a result of variations in the running rate of the machines. vAs a matter of fact, the different elements of the machines have a different caloriilc inertia and reach their thermic equilibrium and consequently their normal expansion conditions only a certain time after the load has been stabilised. When the rate of running varies, the elements of the machine are submitted to a succession of expansions and contractions and this is the case -in particular for the nozzles and distributors forming the stationary bladings; these latter members should remain duid-tight with the exception of the passages left open for the flow of gaseiform iiuid and moreover they must remain correctly centered with reference to the movable blading of the rotor.
'I'he present invention covers an arrangement for mounting the stationary bladings of gas turbines or generally speaking of the bladings of any turbo-machines operating with iiuid at high temperatures; according to the invention, the blades are integral only with a single ring-shaped member and they are mounted on the side opposite to said vring-shaped member in a manner such as will allow radial displacement due to their expansion.
The followingdescription and accompanying corresponding drawings showing by way of example forms of execution ofthe invention, will allow said invention and the manner of executing `in Fig. 1; the diierent expansion of these ringsame to be easily understood; the features appearl ing both in the drawings and in the specification form of course part of said invention.
Fig. 1 is a partial axial cross-section showing the us'ual manner of 'executing stationary distributors, and Figs. 2 to 5 are corresponding views of diiferent forms of execution improved in accordance with said invention. y
Fig. 2 is an axial cross-section of a first type of distributor.
Fig. 3 is a developed cross-section of the stationary blading of said distributor, the crosssection being executed through a coaxial cylinder.
Fig. 4 and 5 are halfcross-sections through shaped members leads-to a compression or to a stretching of the blades.
Fig. 2 shows the application'of the invention to a first distributor or injecting nozzles of a turbine operating with gases or with highly superl heated steam; the driving fiuid enters through Ythe torus d and expands between the blades c of the nozzle and drives the receiving wheel e.
The blades c of the expansion nozzle are provided with two heels or end pieces f and g and are rigidly secured to the outer ring-shaped member i, by means of rivets i for instance. The outer ring-shaped member l is mounted in .its turn in a manner such as will allow its free expansion inside the body h of the stator by means of a radial system of pins or keys k the number of which is at least equal to three.
The duid-tightness of the mounting of the ring-shaped member i inside the stator is provided by the correct machining of the lateral surfaces of said member and of the surfaces of the reess housing it inside the stator h and by the pressure of the driving iluid which applies the ring-shaped member against .the down-stream side surface of its recess.
The fluid-tightnessV at the center of the distributor is provided by a free or iioating ring l bearing, under the action of the pressure of the driving gases passing out of the torus, on one hand against the body of the stator h, on the other against the heels g of the blades. In order to provide for a proper bearing of the ring-shaped member against the heels g, the latter are tted inside one another by means of the arrangement shown in Fig. 3, in which the bearing surfaces between adjacent blades are illustrated as forming a series of steps.
. Figs. 4 and 5 relates more particularly to an intermediary distributor adapted for use either in a gas turbine or in a high pressure steam turbine. Fig. 4 shows more particularly a crosssection through the axis of a blade guiding pin, and Fig. 5 a cross-section through the pin con- `heels f1 of the blades which are not mechanically interconnected engage an outer ring shaped member i1 inside which they are centered by a certain number of pins o the number of which is equal at the utmost to that of the blades. In practice a single pin or key may be provided for a group of two or three' consecutive blades.
. In order to allow said radially arranged pins toslide during the varying heating and consequent expansion of the different elements connected by them, the outer ring-shaped member il is mounted in its turn in a manner such as will allow its free expansion with reference to the stator h of the machine so that the reactions of the stator are prevented from deforming the pin carrying ring-shaped member. The ringshaped member i1 may be guided with reference to the stator by means of radial pins or keys p.
Obviously the above form of execution has been shown solely by way of example and it is possible to modify the forms in various manners chiefly by substituting therefor technical equivalents without widening thereby the scope of the invention as defined by accompanying claims.
What we claim is:
1. In a turbo-machine adapted to operate at high temperatures, the provision of a stationary distributor comprising two coaxial rings, a system of blades arranged between said rings, se-
cured rigidly to only one thereof, and engaging the other ring in amanner allowingv the free'4 expansion of the blades with reference thereto and a stator enclosing the two ring-shaped members, the ring-shaped member rigid with the blades being machined along its lateral surface engaging the stator for providing iluidtightness under the action of fluid pressure and allowing the free'relative expansion of the ring-shaped member with reference to thev stator.
2. In a turbo-machine adapted to `operate at high temperatures, the provision of a stationary distributor comprising two coaxial-rings, a system of blades arranged between said rings, secured rigidly to only one thereof, and engaging the other ring in a manner allowing the free expansion of the blades with reference thereto, a
stator enclosing the two ring-shaped members, the ring-shaped member 1 rigid with the blades being machined along its lateral surface engaging the stator for providing vuid-tightness under the laction of fluid pressure and allowing the free relative expansion of the ring-shaped member with reference to the stator and a system of at least three radial pins rigid with the stator` and engaging freely the ring-shaped member rigid with the blades for centering said member.
3. In a turbo-machineA adaptedv to operate at high temperatures. theprovision of a stationary distributor including a stator, a ringfitted therein, a system of radial blades rigidly secured to said ring and a lsecond floating ring, adapted to bear under the action of gas pressure both against the periphery of the blades opposed to the periphery engaging the first ring and against the stator.
4. In a turbo-machine adapted to operate at high temperatures, the provision of an intermediary distributor including a central ring-shaped member, a system oi radial blades rigidly con- Y manner such as will allow its freev expansion with reference thereto, and radial pins rigid with the stator and freely engaging the outer ring-shaped member for centering same.
5. In a turbo-machine adapted to operate at high temperatures and having a stator and at least one wheel rotatablyl mounted in said stator, the provision of a stationary distributor cooperating with said wheel and comprising an external and an internal ring coaxially disposed with reference to said wheel, the said external ring being mounted in a circular groove of said stator with a peripheral play allowing the radial expansion of said ring, guiding means radially disposed in said stator for centering said ring in said stator with respect to said wheel and for ensuring the radial expansion of said ring in said play, a system of blades arranged between said internal and said external ring, means for securing rigidly said blades to only one of said rings, and means providing a radial fitting with a peripheral play between said blades and said other ring, said fitting comprising, on said ring and on the blades, planes at right angles with 'the axis of said wheel and adapted to be applied Vating with said wheel and comprising an external and an internal ring coaxially disposed with reference to said wheel, thev said external ring being mounted in a circular groove of said stator with a peripheral play allowing the radial ex- 4pansion o'f said ring, guiding means for centering said ring on ysaid stator with respect to said wheel and for ensuring the radial expansion of said ring yin said play, a'system of blades arranged between said interna/l and said external ring, means for securing rigidly said blades to said internal ring, means providing a radial iltting with a peripheral play between the said blades and the external ring andvmeans for centering said blades in said external ring.
7. In a turbo-machine adapted to operatey at high temperatures and having a stator and at least one wheelrotatablymounted in said stator, the provision of a stationary distributor. co-
operating with said wheel and comprising an external and an internal ring coaxially disposed with reference to said wheel, the said external ring being mounted in a circular groove of said stator with a peripheral play allowing the radial expansion of said ring, guiding means radially disposed-on said stator for centering said ring in said stator with respect to said wheel and for ensuring the radial expansion of said ring in said REFERENCES CITED The following references are of record in the ille of this patent:
UNITED STATES PATENTS Number Number Name Date Wagner Mar. 26, 1912 Kieser Sept. 28, 1915 Rice Mar. 25, 1919 Losel June 14, 1927 Downer Apr. 23, 1935 Birmann Sept. 3, 1935 Carlson Mar. 26, 1940 FOREIGN PATENTS Country Date Great Britain Dec. 27, 1923 Great Britain June 25, 1925 Germany Nov. 4, 1926
US626104A 1944-12-05 1945-11-01 Turbine distributor and nozzle Expired - Lifetime US2447942A (en)

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FR994013T 1944-12-05

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GB (1) GB609220A (en)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2530908A (en) * 1946-09-18 1950-11-21 Allis Chalmers Mfg Co Turbine diaphragm
US2643086A (en) * 1947-09-02 1953-06-23 Armstrong Siddeley Motors Ltd Mounting of turbine blades
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2681788A (en) * 1951-05-23 1954-06-22 Solar Aircraft Co Gas turbine vane structure
US2772069A (en) * 1951-10-31 1956-11-27 Gen Motors Corp Segmented stator ring assembly
US2801075A (en) * 1952-12-22 1957-07-30 Gen Motors Corp Turbine nozzle
US2838275A (en) * 1952-10-03 1958-06-10 Vickers Electrical Co Ltd Gas turbines
US2858104A (en) * 1954-02-04 1958-10-28 A V Roe Canada Ltd Adjustable gas turbine shroud ring segments
US2919891A (en) * 1957-06-17 1960-01-05 Gen Electric Gas turbine diaphragm assembly
US2945673A (en) * 1951-10-31 1960-07-19 Gen Motors Corp Segmented stator ring assembly
US3043564A (en) * 1960-03-14 1962-07-10 United Aircraft Corp Stator construction
US3066911A (en) * 1959-05-12 1962-12-04 Thompson Ramo Wooldridge Inc Nozzle and turbine wheel shroud support
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
US3141651A (en) * 1962-08-13 1964-07-21 Gen Electric Turbine shroud structure
US3909155A (en) * 1973-07-06 1975-09-30 Rolls Royce 1971 Ltd Sealing of vaned assemblies
US4025229A (en) * 1975-11-14 1977-05-24 Turbodyne Corporation (Steam Turbine Div.) Diaphragm with cast nozzle blocks and method of construction thereof
US4097188A (en) * 1976-04-15 1978-06-27 Terence Owen Forster Nozzle insert for a turbine
US4245951A (en) * 1978-04-26 1981-01-20 General Motors Corporation Power turbine support
US5037269A (en) * 1990-01-26 1991-08-06 Westinghouse Electric Corp. Self-locking nozzle blocks for steam turbines
US5224825A (en) * 1991-12-26 1993-07-06 General Electric Company Locator pin retention device for floating joint
WO1997001708A1 (en) * 1995-06-29 1997-01-16 Dresser-Rand Company Gas turbine starter
US5964574A (en) * 1997-01-29 1999-10-12 Asea Brown Boveri Ag Exhaust-gas turbine of a turbocharger
EP1536103A1 (en) * 2003-11-28 2005-06-01 BorgWarner Inc. Turbo machine having inlet guide vanes and attachment arrangement therefor
EP1531235A3 (en) * 2003-11-11 2006-01-18 Ansaldo Energia S.P.A. Stator for an axial-flow turbine
EP1724443A1 (en) * 2005-05-20 2006-11-22 ABB Turbo Systems AG Nozzle ring
CN102422027A (en) * 2009-05-07 2012-04-18 斯奈克玛 Housing for a stator of an aircraft turbine engine, comprising slits for the mechanical offloading of blades
US20140147265A1 (en) * 2012-11-29 2014-05-29 Techspace Aero S.A. Axial Turbomachine Blade with Platforms Having an Angular Profile

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1021222A (en) * 1910-11-10 1912-03-26 Gen Electric Bucket-wheel.
US1154777A (en) * 1914-02-21 1915-09-28 Gen Electric Attaching means for nozzles.
US1298564A (en) * 1918-06-12 1919-03-25 Gen Electric Elastic-fluid turbine.
GB208681A (en) * 1923-02-23 1923-12-27 Erste Bruenner Maschinen Fab Improvements in and relating to steam or gas turbines, turbocompressors and the like
GB226798A (en) * 1923-12-24 1925-06-25 Escher Wyss Maschf Ag Improvements in guide apparatus for steam or gas turbines
DE436567C (en) * 1924-01-19 1926-11-04 Waggon Und Maschb Akt Ges Guide vane ring for steam and gas turbines
US1632448A (en) * 1927-06-14 Eeahz losbii
US1998951A (en) * 1933-11-15 1935-04-23 Gen Electric Nozzle diaphragm
US2013512A (en) * 1933-03-11 1935-09-03 Laval Steam Turbine Co Guide vane and diaphragm construction for turbines
US2195325A (en) * 1938-06-06 1940-03-26 Carling Turbine Blower Co Turbine construction

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1632448A (en) * 1927-06-14 Eeahz losbii
US1021222A (en) * 1910-11-10 1912-03-26 Gen Electric Bucket-wheel.
US1154777A (en) * 1914-02-21 1915-09-28 Gen Electric Attaching means for nozzles.
US1298564A (en) * 1918-06-12 1919-03-25 Gen Electric Elastic-fluid turbine.
GB208681A (en) * 1923-02-23 1923-12-27 Erste Bruenner Maschinen Fab Improvements in and relating to steam or gas turbines, turbocompressors and the like
GB226798A (en) * 1923-12-24 1925-06-25 Escher Wyss Maschf Ag Improvements in guide apparatus for steam or gas turbines
DE436567C (en) * 1924-01-19 1926-11-04 Waggon Und Maschb Akt Ges Guide vane ring for steam and gas turbines
US2013512A (en) * 1933-03-11 1935-09-03 Laval Steam Turbine Co Guide vane and diaphragm construction for turbines
US1998951A (en) * 1933-11-15 1935-04-23 Gen Electric Nozzle diaphragm
US2195325A (en) * 1938-06-06 1940-03-26 Carling Turbine Blower Co Turbine construction

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2530908A (en) * 1946-09-18 1950-11-21 Allis Chalmers Mfg Co Turbine diaphragm
US2643086A (en) * 1947-09-02 1953-06-23 Armstrong Siddeley Motors Ltd Mounting of turbine blades
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2681788A (en) * 1951-05-23 1954-06-22 Solar Aircraft Co Gas turbine vane structure
US2945673A (en) * 1951-10-31 1960-07-19 Gen Motors Corp Segmented stator ring assembly
US2772069A (en) * 1951-10-31 1956-11-27 Gen Motors Corp Segmented stator ring assembly
US2838275A (en) * 1952-10-03 1958-06-10 Vickers Electrical Co Ltd Gas turbines
US2801075A (en) * 1952-12-22 1957-07-30 Gen Motors Corp Turbine nozzle
US2858104A (en) * 1954-02-04 1958-10-28 A V Roe Canada Ltd Adjustable gas turbine shroud ring segments
US2919891A (en) * 1957-06-17 1960-01-05 Gen Electric Gas turbine diaphragm assembly
US3066911A (en) * 1959-05-12 1962-12-04 Thompson Ramo Wooldridge Inc Nozzle and turbine wheel shroud support
US3043564A (en) * 1960-03-14 1962-07-10 United Aircraft Corp Stator construction
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
US3141651A (en) * 1962-08-13 1964-07-21 Gen Electric Turbine shroud structure
US3909155A (en) * 1973-07-06 1975-09-30 Rolls Royce 1971 Ltd Sealing of vaned assemblies
US4092768A (en) * 1975-11-14 1978-06-06 Turbodyne Corporation (Steam Turbine Division) Method for making a diaphragm with cast nozzle blocks
US4025229A (en) * 1975-11-14 1977-05-24 Turbodyne Corporation (Steam Turbine Div.) Diaphragm with cast nozzle blocks and method of construction thereof
US4097188A (en) * 1976-04-15 1978-06-27 Terence Owen Forster Nozzle insert for a turbine
US4245951A (en) * 1978-04-26 1981-01-20 General Motors Corporation Power turbine support
US5037269A (en) * 1990-01-26 1991-08-06 Westinghouse Electric Corp. Self-locking nozzle blocks for steam turbines
US5224825A (en) * 1991-12-26 1993-07-06 General Electric Company Locator pin retention device for floating joint
WO1997001708A1 (en) * 1995-06-29 1997-01-16 Dresser-Rand Company Gas turbine starter
US5964574A (en) * 1997-01-29 1999-10-12 Asea Brown Boveri Ag Exhaust-gas turbine of a turbocharger
EP0856639A3 (en) * 1997-01-29 2000-04-19 Asea Brown Boveri AG Nozzle ring for a radial turbine
EP1531235A3 (en) * 2003-11-11 2006-01-18 Ansaldo Energia S.P.A. Stator for an axial-flow turbine
EP1536103A1 (en) * 2003-11-28 2005-06-01 BorgWarner Inc. Turbo machine having inlet guide vanes and attachment arrangement therefor
US20060034684A1 (en) * 2003-11-28 2006-02-16 Dietmar Metz Fluid flow engine and support ring for it
US7189058B2 (en) 2003-11-28 2007-03-13 Borg Warner Inc. Fluid flow engine and support ring for it
EP1724443A1 (en) * 2005-05-20 2006-11-22 ABB Turbo Systems AG Nozzle ring
WO2006122438A1 (en) * 2005-05-20 2006-11-23 Abb Turbo Systems Ag Nozzle ring
CN102422027A (en) * 2009-05-07 2012-04-18 斯奈克玛 Housing for a stator of an aircraft turbine engine, comprising slits for the mechanical offloading of blades
CN102422027B (en) * 2009-05-07 2015-05-13 斯奈克玛 Housing for a stator of an aircraft turbine engine, comprising slits for the mechanical offloading of blades
US20140147265A1 (en) * 2012-11-29 2014-05-29 Techspace Aero S.A. Axial Turbomachine Blade with Platforms Having an Angular Profile
US10202859B2 (en) * 2012-11-29 2019-02-12 Safran Aero Boosters Sa Axial turbomachine blade with platforms having an angular profile

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Publication number Publication date
FR994013A (en) 1951-11-09
GB609220A (en) 1948-09-28

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