US3824034A - Guide blade ring - Google Patents

Guide blade ring Download PDF

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Publication number
US3824034A
US3824034A US00248094A US24809472A US3824034A US 3824034 A US3824034 A US 3824034A US 00248094 A US00248094 A US 00248094A US 24809472 A US24809472 A US 24809472A US 3824034 A US3824034 A US 3824034A
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US
United States
Prior art keywords
segments
housing
arrangement according
cover ring
guide blade
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
US00248094A
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English (en)
Inventor
W Leicht
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.)
Rolls Royce Solutions GmbH
Original Assignee
MTU Friedrichshafen GmbH
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 MTU Friedrichshafen GmbH filed Critical MTU Friedrichshafen GmbH
Application granted granted Critical
Publication of US3824034A publication Critical patent/US3824034A/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

  • a guide blade ring which divided into segments is secured at the gas guide housing of an axial turbine, for example, of an exhaust-gas turbo-supercharger for a reciprocating internal combustion engine, in which the joints between the individual segments form in the cold condition air gaps that extend approximately in the direction of the blade inlet angle; each segment includes a radially inwardly extending flange at which the respective segment is secured by means of two bolts between an inner cover ring and the gas guide housing whereby the inner cover ring assumes the radial centering function of the segments and the sealing function for the inner joint gaps; a centering bushing is arranged in one of the two bolt bores which surrounds the respective bolt with a spacing and connects with each other the flange and the gas guide housing while simultaneously determining also. the position of the segments in the circumferential direction; the bolt bore for the respective other bolt of each segment surround
  • the present invention relates to a guide blade ring which subdivided into segments is secured at the gas guide housing of an axial turbine, for example, of an exhaust gas turbo-supercharger for a reciprocating piston internal combustion engine, whereby the joints between the individual segments, in which an air gap is present in the cold condition, extend approximately in the direction of the blade inlet angle.
  • the fastening of the guide blades at the gas guide housing therefore has to be so constructed that no compulsive forces can result especially by reason of the occurring large and differing thermal expansions.
  • the guide blades are combined, for example, into a closed ring which is threadably connected with the gas guide housing.
  • closed rings are very limited in their free expansion possibility so that with differing thermal loads it may lead to stress cracks and compulsive forces are exerted on the housing.
  • a construction is also known in the prior art in which a guide blade ring is subdivided into segments.
  • the inner and outer casing parts of the segments are axially extended opposite the flow direction and are inserted into corresponding ring slots for the purpose of sealing the flow space for the propulsion gas against the cooling medium spaces.
  • the segments are prevented I in their free expansion.
  • each segment includes a radially inwardly extending flange, at which it is secured by means of two bolts between an inner cover ring and the gas guide housing, whereby the inner cover ring assumes the radial centering of the segments and the sealing of the inner joint gaps, and in that in one of the two bolt bores a centering bushing is arrangedsurrounding the bolt with a spacing, which connects with each other the flange and gas guide housing and determines the position of the segments in the circumferential direction whereas the bolt bore for the respective other bolt surrounds the same with a gap.
  • the outer joint gaps . are sealed by an outer cover ring which is equipped with an axial abutment surface for the outer casing portion of theguide blade segments and which in the cold condition surrounds the assembled guide blade ring axially to the abutment surface and radially with a gap.
  • one relief slot each is arranged in the outer casing portion of each segment at each second blade channel, which extends approximately in the direction of the blade inlet angle.
  • FIG. 1 is a partial longitudinal cross-sectional view through an axial turbine and guide blade ring in accordance with the present invention
  • FIG. 2 is a front elevational view of an individual guide blade segment
  • FIG. 3 is a partial plan view on a relief slot in the outer casing portion of a guide blade segment in accordance with the present invention.
  • a guide blade ring 17 subdivided into segments 11 is secured at the gas guide housing 16 of a conventional exhaust-gas turbo-supercharger (not shown) at a radially inwardly extending flange 18 by means of an inner cover ring 12which seals the inner jointgaps against gas losses, and by means of two bolts 15.
  • the inner cover ring 12 takes over together with two centering seats 19, 20, the radial centering of the segments 11.
  • the determination of the segments 11 in the circumferential direction takes place by one centering sleeve 14 each arranged in a respective bolt bore 21, which connects with each other the flange 18 and the gas .guide housing 16 and which surrounds the bolt 15 with a gap.
  • the bore 22 for the respective other bolt is constructed as sufficiently large through-bore.
  • One relief slot 24each is arranged in the outer casing portion 23 of each segment 11 at each second blade channel, which relief slot extends approximately in the direction of the blade inlet angle. A bending stress of the guide blades as a result of the larger thermal expan- .sion of the outer casing portion 23 with respect to the shorter inner casing portion 25 is effectively avoided thereby.
  • An outer cover ring 13 which seals the outer joint gaps between the segments 11 and the relief slots 24 against gas losses, is provided with an axial abutment surface 26 for the outer casing portion 23 of the segments 11 and surrounds in the cold condition the assembled guide blade ring 17 axially with respect to the abutment surface 26 and radially with a gap, whence also in the radial and axial direction the thermal expansion of the segments 11 can take place unimpairedly without the possibility that any compulsive forces or stresses can occur.
  • a guide blade ring formed of a plurality of segments with joints between individual segments forming respective air gaps in the cold condition of said guide blade ring, each of said segments including a radially inwardly extending flange means,
  • an inner cover ring means separate from said housing for radially centering said segments with respect to said housing and for sealing radially inner portions of said gaps between said segments, said inner cover ring means including a radially outwardly facing surface for radially centering said segments with respect to said housing, said bolts being positioned for clamping said inner cover ring means together with said flange means to said housing.
  • a centering bush means is arranged in one of the two bolt bores of each flange means, said centering bush means being in surrounding relationship to and spaced from the one of said bolts in said bore, said centering bush means being in engagement with said housing and said respective flange for maintaining the respective segment in a predetermined circumferential position with respect to said housing, the other of said bolt bores being larger than the bolt therein to form a gap for permitting thermal expansion.
  • An arrangement according to claim 1 further comprising an outer cover ring means for sealing radially outer portions of said gaps between said segments, said outer cover ring means including an axially facing abutment surface which is engageable with outer casing portions of said segments, said outer cover ring means being dimensioned and configured such that it surrounds said segments with an axial and radial spacing in the cold condition of said guide blade ring.
  • each segment includes a plurality of said relief slots.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
US00248094A 1971-05-03 1972-04-27 Guide blade ring Expired - Lifetime US3824034A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2121707A DE2121707C3 (de) 1971-05-03 1971-05-03 Leitschaufelkranz

Publications (1)

Publication Number Publication Date
US3824034A true US3824034A (en) 1974-07-16

Family

ID=5806680

Family Applications (1)

Application Number Title Priority Date Filing Date
US00248094A Expired - Lifetime US3824034A (en) 1971-05-03 1972-04-27 Guide blade ring

Country Status (9)

Country Link
US (1) US3824034A (de)
JP (1) JPS5218850B1 (de)
AT (1) AT311737B (de)
CH (1) CH538045A (de)
DE (1) DE2121707C3 (de)
ES (1) ES402257A1 (de)
FR (1) FR2136773A5 (de)
GB (1) GB1344221A (de)
IT (1) IT952754B (de)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3909155A (en) * 1973-07-06 1975-09-30 Rolls Royce 1971 Ltd Sealing of vaned assemblies
US4194869A (en) * 1978-06-29 1980-03-25 United Technologies Corporation Stator vane cluster
US4566851A (en) * 1984-05-11 1986-01-28 United Technologies Corporation First stage turbine vane support structure
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
US4650396A (en) * 1984-01-09 1987-03-17 Bbc Brown, Boveri & Company, Limited Externally adjustable axial location for a vane carrier in a turbine
US4721434A (en) * 1986-12-03 1988-01-26 United Technologies Corporation Damping means for a stator
US4890978A (en) * 1988-10-19 1990-01-02 Westinghouse Electric Corp. Method and apparatus for vane segment support and alignment in combustion turbines
US4904156A (en) * 1987-12-16 1990-02-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Screwed attachment of a body of revolution to an annular flange in a turbine engine
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
US5392513A (en) * 1993-12-21 1995-02-28 General Electric Co. Steampath and process of retrofitting a nozzle thereof
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
US5618161A (en) * 1995-10-17 1997-04-08 Westinghouse Electric Corporation Apparatus for restraining motion of a turbo-machine stationary vane
US6234750B1 (en) * 1999-03-12 2001-05-22 General Electric Company Interlocked compressor stator
EP1319844A1 (de) * 2001-12-13 2003-06-18 Rolls-Royce Deutschland Ltd & Co KG Lagerring zur Lagerung von Schaufelfüssen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
EP1724443A1 (de) * 2005-05-20 2006-11-22 ABB Turbo Systems AG Düsenring
US20080295516A1 (en) * 2004-10-29 2008-12-04 Takanori Teshima Turbocharger
US20100310358A1 (en) * 2009-06-05 2010-12-09 Major Daniel W Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US8757966B2 (en) 2008-08-26 2014-06-24 Snecma Stationary vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such stationary vane assembly
US20140208741A1 (en) * 2013-01-31 2014-07-31 Electro-Motive Diesel, Inc. Turbocharger with axial turbine stage
US9739176B2 (en) 2013-10-24 2017-08-22 Man Diesel & Turbo Se Turbomachine
US20170306776A1 (en) * 2016-04-21 2017-10-26 United Technologies Corporation Fastener retention mechanism
US10914196B2 (en) 2015-11-27 2021-02-09 Safran Aircraft Engines Module of a turbomachine or of a combustion chamber test bench

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010064047A1 (de) * 2010-12-23 2012-06-28 Man Diesel & Turbo Se Strömungsmaschine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2905434A (en) * 1954-07-08 1959-09-22 Westinghouse Electric Corp Turbine apparatus
US3262677A (en) * 1963-11-27 1966-07-26 Gen Electric Stator assembly
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2905434A (en) * 1954-07-08 1959-09-22 Westinghouse Electric Corp Turbine apparatus
US3262677A (en) * 1963-11-27 1966-07-26 Gen Electric Stator assembly
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3909155A (en) * 1973-07-06 1975-09-30 Rolls Royce 1971 Ltd Sealing of vaned assemblies
US4194869A (en) * 1978-06-29 1980-03-25 United Technologies Corporation Stator vane cluster
US4650396A (en) * 1984-01-09 1987-03-17 Bbc Brown, Boveri & Company, Limited Externally adjustable axial location for a vane carrier in a turbine
US4566851A (en) * 1984-05-11 1986-01-28 United Technologies Corporation First stage turbine vane support structure
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
US4721434A (en) * 1986-12-03 1988-01-26 United Technologies Corporation Damping means for a stator
US4904156A (en) * 1987-12-16 1990-02-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Screwed attachment of a body of revolution to an annular flange in a turbine engine
US4890978A (en) * 1988-10-19 1990-01-02 Westinghouse Electric Corp. Method and apparatus for vane segment support and alignment in combustion turbines
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
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
US5392513A (en) * 1993-12-21 1995-02-28 General Electric Co. Steampath and process of retrofitting a nozzle thereof
US5618161A (en) * 1995-10-17 1997-04-08 Westinghouse Electric Corporation Apparatus for restraining motion of a turbo-machine stationary vane
US6234750B1 (en) * 1999-03-12 2001-05-22 General Electric Company Interlocked compressor stator
US6790000B2 (en) 2001-12-13 2004-09-14 Rolls-Royce Deutschland Ltd & Co Kg Shroud for the roots of variable stator vanes in the high-pressure compressor of a gas turbine
EP1319844A1 (de) * 2001-12-13 2003-06-18 Rolls-Royce Deutschland Ltd & Co KG Lagerring zur Lagerung von Schaufelfüssen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
US20080295516A1 (en) * 2004-10-29 2008-12-04 Takanori Teshima Turbocharger
EP1724443A1 (de) * 2005-05-20 2006-11-22 ABB Turbo Systems AG Düsenring
WO2006122438A1 (de) * 2005-05-20 2006-11-23 Abb Turbo Systems Ag Düsenring
US8757966B2 (en) 2008-08-26 2014-06-24 Snecma Stationary vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such stationary vane assembly
US8328512B2 (en) * 2009-06-05 2012-12-11 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US20100310358A1 (en) * 2009-06-05 2010-12-09 Major Daniel W Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US8951010B2 (en) 2009-06-05 2015-02-10 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US20140208741A1 (en) * 2013-01-31 2014-07-31 Electro-Motive Diesel, Inc. Turbocharger with axial turbine stage
US9181855B2 (en) * 2013-01-31 2015-11-10 Electro-Motive Diesel, Inc. Turbocharger with axial turbine stage
US9739176B2 (en) 2013-10-24 2017-08-22 Man Diesel & Turbo Se Turbomachine
US10914196B2 (en) 2015-11-27 2021-02-09 Safran Aircraft Engines Module of a turbomachine or of a combustion chamber test bench
US20170306776A1 (en) * 2016-04-21 2017-10-26 United Technologies Corporation Fastener retention mechanism
US10294808B2 (en) * 2016-04-21 2019-05-21 United Technologies Corporation Fastener retention mechanism

Also Published As

Publication number Publication date
GB1344221A (en) 1974-01-16
CH538045A (de) 1973-06-15
DE2121707A1 (de) 1972-11-16
DE2121707C3 (de) 1974-06-20
DE2121707B2 (de) 1973-11-22
AT311737B (de) 1973-11-26
JPS5218850B1 (de) 1977-05-24
FR2136773A5 (de) 1972-12-22
IT952754B (it) 1973-07-30
ES402257A1 (es) 1975-11-01

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