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US2801076A - Turbine nozzles - Google Patents

Turbine nozzles Download PDF

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Publication number
US2801076A
US2801076A US378927A US37892753A US2801076A US 2801076 A US2801076 A US 2801076A US 378927 A US378927 A US 378927A US 37892753 A US37892753 A US 37892753A US 2801076 A US2801076 A US 2801076A
Authority
US
United States
Prior art keywords
blades
blade
recesses
turbine nozzles
turbine
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
US378927A
Other languages
English (en)
Inventor
Terrell Basil Joseph
Darling Robert Francis
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.)
Parsons and Marine Engineering Turbine Research and Development Association
Original Assignee
Individual
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 Individual filed Critical Individual
Application granted granted Critical
Publication of US2801076A publication Critical patent/US2801076A/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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics

Definitions

  • This invention relates to nozzles, i. e. fixed blades foi turbines where the inlet temperature is too high to permit the use of uncooled steels or metallic alloys.
  • the invention consists in a turbine nozzle assembly having features as set forth in the claims appended hereto.
  • Figure 1 is an end elevation view of part of a ring of xed nozzle blades with mounting assembly.
  • Figure 2 is an enlarged end elevation view of one of the outer annulus elements thereof.
  • Figure 3 is a cross-section view on the line III--III of Figure 2.
  • Figure 4 is a developed plan view of the element of Figure 2.
  • Figure 5 is an enlarged end elevation view of one of the inner annulus elements.
  • Figure 6 is a cross-section View on the line VI-VI of Figure 5.
  • Figure 7 is a developed plan view of the element of Figure 5.
  • Figure 8 is a sectional elevational view through the nozzle ring.
  • Figure 9 is an elevational View of an individual blade of a modification.
  • Figure 10 is an end view of the individual blade of Figure 9, viewed from one of the open ends of the blade and showing the hollow interior thereof, and
  • Figure 11 is an enlarged fragmentary section on the line Xl--JG of Fig. 8.
  • a nozzle assembly comprises 72 separate hollow blades a of ceramic material, each blade being open at both its inner and outer ends and being supported in radial positions between an outer annulus and an inner concentric annulus.
  • the outer annulus comprises 12 segmental members b also of ceramic material, and the inner annulus comprises 12 segmental members c.
  • Both sets of annuli are furnished with interlocking ends and the outer set is furnished with external grooves d to form a circumferential groove into which a bonding wire e is tted and the ends welded together at f ( Figure ll).
  • the opposing faces of the segments b, c comprising the outer and inner concentric annuli are furnished with recesses g, h respectively into which the respective ends of each blade a are itted in such a way as to be free to expand both lengthwise and chordwise.
  • This is effected ice by shaping the recesses g and h to afford clearance in a circumferential direction between the blade end and at least one of the side walls of the recess in which said blade end is received, and also by arranging the recesses in the segments b and c to afford end clearance for the blade as shown in Fig. 8.
  • the purpose of using hollow blades is that under conditions of rapidly-changing temperature the various portions of the blade are at substantially the same temperature at any given instant, thus avoiding thermal stresses that would be involved in the case of solid blades where the central portions would warm up or cool down much more slowly than the surface layers.
  • the fact of the blades being open at both ends avoids the stresses which would be set up if the ends were closed.
  • the blade ends for occupying the recesses may be sprayed with metal to enhance uniformity of distribution of the supporting stresses.
  • the sprayed area is indicated at a in Fig. 9.
  • a turbine nozzle assembly comprising hollow blades of ceramic material open at both ends, and supporting pieces of non-metallic material having recesses therein receiving the ends of the blades and supporting the latter, said recesses having walls following the contours of the said ends for holding the said ends in position and being spaced circumferentially from the said ends to afford clearance in a circumferential direction between the ends of the blades and the recesses receiving such ends, and means holding the said supporting pieces together to form two annuli, the recesses thereof facing respectively outwardly and inwardly and being spaced from the respective axes of the annuli by distances diiering by more than the length of the blades, and thus providing end clearance between the ends of the blades and the bottoms of the said recesses, whereby the blades are free to expand both lengthwise and chordwise.
  • a turbine nozzle assembly as claimed in claim l wherein said supporting pieces comprises concentric rings of segments, the segments of each ring being shaped to interlock with one another at their ends.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US378927A 1952-11-18 1953-09-08 Turbine nozzles Expired - Lifetime US2801076A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29138/52A GB723505A (en) 1952-11-18 1952-11-18 Improvements in or relating to turbine nozzles

Publications (1)

Publication Number Publication Date
US2801076A true US2801076A (en) 1957-07-30

Family

ID=10332360

Family Applications (1)

Application Number Title Priority Date Filing Date
US378927A Expired - Lifetime US2801076A (en) 1952-11-18 1953-09-08 Turbine nozzles

Country Status (5)

Country Link
US (1) US2801076A (de)
CH (1) CH320493A (de)
DE (1) DE958888C (de)
FR (1) FR1083337A (de)
GB (1) GB723505A (de)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
US3378228A (en) * 1966-04-04 1968-04-16 Rolls Royce Blades for mounting in fluid flow ducts
US3857649A (en) * 1973-08-09 1974-12-31 Westinghouse Electric Corp Inlet vane structure for turbines
USB563412I5 (de) * 1975-03-28 1976-02-24
US3943703A (en) * 1973-05-22 1976-03-16 United Turbine AB and Co., Kommanditbolag Cooling passages through resilient clamping members in a gas turbine power plant
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator
US4180371A (en) * 1978-03-22 1979-12-25 Avco Corporation Composite metal-ceramic turbine nozzle
US4477222A (en) * 1982-09-30 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Mounting construction for turbine vane assembly
US4876849A (en) * 1986-11-20 1989-10-31 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Gas turbine propulsion unit with a gas generator
US5037273A (en) * 1988-12-19 1991-08-06 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Compressor impeller
DE4100224A1 (de) * 1991-01-07 1992-07-09 Daimler Benz Ag Halterung eines diffusors einer gasturbine im turbinengehaeuse
US5634768A (en) * 1994-11-15 1997-06-03 Solar Turbines Incorporated Airfoil nozzle and shroud assembly
EP0899426A2 (de) * 1997-08-23 1999-03-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Leitschaufel für eine Gasturbine
US20060045747A1 (en) * 2004-08-30 2006-03-02 General Electric Company Compressor stator floating tip shroud and related method

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2917276A (en) * 1955-02-28 1959-12-15 Orenda Engines Ltd Segmented stator ring assembly
US2914300A (en) * 1955-12-22 1959-11-24 Gen Electric Nozzle vane support for turbines
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3015524A (en) * 1958-11-19 1962-01-02 Owens Corning Fiberglass Corp Inverted turbine
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US3132842A (en) * 1962-04-13 1964-05-12 Gen Electric Turbine bucket supporting structure
CH489699A (de) * 1968-03-22 1970-04-30 Sulzer Ag Leitschaufelkranz für Turbomaschinen
DE2918874C2 (de) * 1979-05-08 1987-04-16 Avco Corp., Greenwich, Conn. Leitschaufelkranz
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
CH663447A5 (de) * 1984-05-16 1987-12-15 Escher Wyss Ag Turbomaschine mit wenigstens einem radial durchstroemten laufrad.
US5584652A (en) * 1995-01-06 1996-12-17 Solar Turbines Incorporated Ceramic turbine nozzle

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1154777A (en) * 1914-02-21 1915-09-28 Gen Electric Attaching means for nozzles.
US2341664A (en) * 1939-12-27 1944-02-15 Schutte Alfred Casing for gas turbines
US2402418A (en) * 1943-01-20 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
US2497041A (en) * 1945-03-27 1950-02-07 United Aircraft Corp Nozzle ring for gas turbines
GB664986A (en) * 1948-10-29 1952-01-16 Maschf Augsburg Nuernberg Ag Ceramic blade for turbines
US2625013A (en) * 1948-11-27 1953-01-13 Gen Electric Gas turbine nozzle structure

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE757505C (de) * 1940-06-13 1954-03-15 Messerschmitt Boelkow Blohm Axial beaufschlagte Leitvorrichtung fuer Kreiselmaschinen, insbesondere Turbinen hoher Waermebelastung
DE886676C (de) * 1940-09-15 1953-08-17 Maschf Augsburg Nuernberg Ag Befestigung von Turbinenschaufeln aus keramischem Werkstoff in einem keramischen Laufrad oder einem keramischen Leitkranz
GB619634A (en) * 1946-12-17 1949-03-11 Nolan Peter William Moore Improvements relating to internal combustion turbines and like apparatus working with gases at high temperatures
BE492385A (de) * 1948-11-27
GB666537A (en) * 1949-08-27 1952-02-13 Armstrong Siddeley Motors Ltd Mounting of the stator blades of a gaseous fluid turbine
BE498667A (de) * 1949-08-27

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1154777A (en) * 1914-02-21 1915-09-28 Gen Electric Attaching means for nozzles.
US2341664A (en) * 1939-12-27 1944-02-15 Schutte Alfred Casing for gas turbines
US2402418A (en) * 1943-01-20 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
US2497041A (en) * 1945-03-27 1950-02-07 United Aircraft Corp Nozzle ring for gas turbines
GB664986A (en) * 1948-10-29 1952-01-16 Maschf Augsburg Nuernberg Ag Ceramic blade for turbines
US2625013A (en) * 1948-11-27 1953-01-13 Gen Electric Gas turbine nozzle structure

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
US3378228A (en) * 1966-04-04 1968-04-16 Rolls Royce Blades for mounting in fluid flow ducts
US3943703A (en) * 1973-05-22 1976-03-16 United Turbine AB and Co., Kommanditbolag Cooling passages through resilient clamping members in a gas turbine power plant
US3857649A (en) * 1973-08-09 1974-12-31 Westinghouse Electric Corp Inlet vane structure for turbines
USB563412I5 (de) * 1975-03-28 1976-02-24
US3992127A (en) * 1975-03-28 1976-11-16 Westinghouse Electric Corporation Stator vane assembly for gas turbines
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator
US4180371A (en) * 1978-03-22 1979-12-25 Avco Corporation Composite metal-ceramic turbine nozzle
US4477222A (en) * 1982-09-30 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Mounting construction for turbine vane assembly
US4876849A (en) * 1986-11-20 1989-10-31 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Gas turbine propulsion unit with a gas generator
US5037273A (en) * 1988-12-19 1991-08-06 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Compressor impeller
DE4100224A1 (de) * 1991-01-07 1992-07-09 Daimler Benz Ag Halterung eines diffusors einer gasturbine im turbinengehaeuse
US5634768A (en) * 1994-11-15 1997-06-03 Solar Turbines Incorporated Airfoil nozzle and shroud assembly
EP0899426A2 (de) * 1997-08-23 1999-03-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Leitschaufel für eine Gasturbine
EP0899426A3 (de) * 1997-08-23 1999-12-08 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Leitschaufel für eine Gasturbine
US20060045747A1 (en) * 2004-08-30 2006-03-02 General Electric Company Compressor stator floating tip shroud and related method
US7195453B2 (en) * 2004-08-30 2007-03-27 General Electric Company Compressor stator floating tip shroud and related method

Also Published As

Publication number Publication date
FR1083337A (fr) 1955-01-07
CH320493A (de) 1957-03-31
GB723505A (en) 1955-02-09
DE958888C (de) 1957-02-28

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