US3790299A - Apparatus for adjusting tip clearance in fluid flow machines - Google Patents

Apparatus for adjusting tip clearance in fluid flow machines Download PDF

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Publication number
US3790299A
US3790299A US00298235A US3790299DA US3790299A US 3790299 A US3790299 A US 3790299A US 00298235 A US00298235 A US 00298235A US 3790299D A US3790299D A US 3790299DA US 3790299 A US3790299 A US 3790299A
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US
United States
Prior art keywords
blading
stator
rotor
adjacent rows
ring
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
US00298235A
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English (en)
Inventor
E Sidler
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
Bbc Brown Boveri & Cie
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Publication date
Application filed by Bbc Brown Boveri & Cie filed Critical Bbc Brown Boveri & Cie
Application granted granted Critical
Publication of US3790299A publication Critical patent/US3790299A/en
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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
    • 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

Definitions

  • ABSTRACT A fluid flow machine of the type wherein adjacent rows of rotor blading rotate between adjacent rows of blading carried by the stator and wherein a ring formed from arcuate intermediate pieces fitted to the stator blading carrier intermediate adjacent rows of stator blading functions as a heat storage member and also forms a space separate from the flow passage for cooling stator blading carrier.
  • the inner periphery of the ring of intermediate pieces establishes a running clearance with the tips of the rotor blading and this clearance is made adjustable by the insertion of packing strips between key portions formed on the intermediate pieces and the walls of circular grooves formed in the stator blading carrier in which these key portions are secured.
  • the procedure for adjusting the tip clearance has usually been that the fully assembled rotor is laid in the casing, also fully assembled, the surfaces around the circumference between the blade rows being lined with strips of lead. When the rotor is placed in position, the blade ends are pressed into the lead strips. When the rotor is removed from the casing the actual clearances between the blade ends and the surface of the casing can be determined from the remaining deformation of the lead strips. On the basis of measurements the rotors and/or blade ends are then machined again, i.e., the blade tips are returned or reground.
  • the primary object of the present invention is therefore to avoid the time and expense of reworking and repeated measurement.
  • the intermediate pieces provided between the rows of stator blading are provided with keys located in circumferential grooves, undercut on at least one side, in the stator blade carrier, the groove containing not only the key but also packing strips of such dimensions that the clearance along the blade tip is virtually uniform and the inclination of the surface of rotation of the rotor is equal to that of the surface formed by the intermediate pieces.
  • the technical improvement offered by the invention lies not only in the fact that the packing strips can easily be manipulated, but also that the tip clearance can be matched in optimum manner to each individual row of rotor blades. In this way the efficiency can be improved because windage losses can be significantly reduced by decreasing the actual clearance.
  • a further advantage is attained when materials are used for the stator and rotor blades which, because the blades have been hardened or provided with a protective coating, do not allow reworking. Particularly in the case of inchromized rotor blades the surface and structure must not be disturbed at any point. This advantage is also important when plastics materials with protective coatings are used.
  • the rotor l is fitted with moving blades 2 which are located in slots around the shaft and secured by means of a root fixing.
  • the stator blade carrier 3 is mounted I in theouter casing and in addition to the circumferential grooves 5 in which the stator blades 4 are fixed, incorporates further circumferential grooves 6.
  • a ring formed from arcuate intermediate pieces 7 is anchored in the circumferential grooves 6 by means of key 8 thereon so that the intermediate pieces 7 form a partition between the flow passage 9 existing between the rotor and stator blading 2,4 and a circumferential cooling-gas space 10 located radially outward of the ring of intermediate pieces 7.
  • the individual intermediate pieces 7 include manufacturing tolerances, in the same way as the other components, such as rotor blades 2, the shaft, stator blade carrier 3, etc. These tolerances must be compensated by tip clearance a, the purpose of which is also to compensate thermal expansion.
  • the circumferential grooves 6 are undercut on one side, providing a circumferential recess 11 into which the packing strips 12 and 12 are inserted.
  • the thickness of the packing strips 12 and 12 is made such that the inclination a of the conical surface formed by the inner periphery of the ring of intermediate pieces 7 is equal to the inclination a of the adjacent rotor blade tip. This also has the effect of making clearance a uniform along the end of the blade profile.
  • a fluid flow machine comprising a rotor provided with adjacent rows of blading rotatable between adjacent rows of blading carried by a stator, a ring formed from arcuate pieces fitted to the stator blading carrier intermediate adjacent rows of the stator blading, the inner periphery of said ring of arcuate intermediate pieces being inclined in the axial direction of the rotor and confronting an inclined peripheral surface of rotasaid arcuate intermediate pieces, said packing strips being dimensioned such that said running clearance along the blade tip is uniform and the inclination of the peripheral surface of rotation formed by the tips of said rotor blading is equal to that of the inner periphery of said ring of arcuate intermediate pieces.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00298235A 1971-11-10 1972-10-17 Apparatus for adjusting tip clearance in fluid flow machines Expired - Lifetime US3790299A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1625571A CH538046A (de) 1971-11-10 1971-11-10 Einrichtung zum Einstellen des Spitzenspiels an Strömungsmaschinen

Publications (1)

Publication Number Publication Date
US3790299A true US3790299A (en) 1974-02-05

Family

ID=4415730

Family Applications (1)

Application Number Title Priority Date Filing Date
US00298235A Expired - Lifetime US3790299A (en) 1971-11-10 1972-10-17 Apparatus for adjusting tip clearance in fluid flow machines

Country Status (7)

Country Link
US (1) US3790299A (it)
JP (1) JPS559522B2 (it)
CH (1) CH538046A (it)
DE (1) DE2159080C3 (it)
FR (1) FR2159378B3 (it)
GB (1) GB1406098A (it)
IT (1) IT970271B (it)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
EP0959229A3 (en) * 1998-05-19 2000-04-12 General Electric Company Low strain shroud element for a turbine
CN100400797C (zh) * 2001-04-12 2008-07-09 西门子公司 具有可轴向相对移动的引导部件的燃气轮机
US8932009B2 (en) 2009-09-04 2015-01-13 Turbomeca Device for supporting a turbine ring, turbine having such a device, and turbine engine having such a turbine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119452A (en) * 1982-04-27 1983-11-16 Rolls Royce Shroud assemblies for axial flow turbomachine rotors
US4645417A (en) * 1984-02-06 1987-02-24 General Electric Company Compressor casing recess
US6315519B1 (en) 1998-09-28 2001-11-13 General Electric Company Turbine inner shroud and turbine assembly containing such inner shroud
FR2949809B1 (fr) * 2009-09-04 2011-11-18 Turbomeca Anneau de turbine, turbine avec un tel anneau et turbomoteur avec une telle turbine
GB201309580D0 (en) * 2013-05-29 2013-07-10 Siemens Ag Rotor tip clearance
US10655491B2 (en) * 2017-02-22 2020-05-19 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine with radial retention features

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA468847A (en) * 1950-10-17 William Walton Morley Frederick Axial compressors
US2722373A (en) * 1951-02-06 1955-11-01 United Aircraft Corp Compressor casing and stator assembly
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
DE1162384B (de) * 1959-07-10 1964-02-06 Licentia Gmbh Ungeschlitzter austenitischer Dichtungsring fuer ferritisches Dampfturbinengehaeuse

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA468847A (en) * 1950-10-17 William Walton Morley Frederick Axial compressors
US2722373A (en) * 1951-02-06 1955-11-01 United Aircraft Corp Compressor casing and stator assembly
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
DE1162384B (de) * 1959-07-10 1964-02-06 Licentia Gmbh Ungeschlitzter austenitischer Dichtungsring fuer ferritisches Dampfturbinengehaeuse

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
EP0959229A3 (en) * 1998-05-19 2000-04-12 General Electric Company Low strain shroud element for a turbine
CN100400797C (zh) * 2001-04-12 2008-07-09 西门子公司 具有可轴向相对移动的引导部件的燃气轮机
US8932009B2 (en) 2009-09-04 2015-01-13 Turbomeca Device for supporting a turbine ring, turbine having such a device, and turbine engine having such a turbine

Also Published As

Publication number Publication date
DE2159080C3 (de) 1980-07-03
FR2159378A1 (it) 1973-06-22
FR2159378B3 (it) 1975-11-28
CH538046A (de) 1973-06-15
JPS4854307A (it) 1973-07-31
JPS559522B2 (it) 1980-03-11
DE2159080A1 (de) 1973-05-17
DE2159080B2 (de) 1979-10-18
GB1406098A (en) 1975-09-17
IT970271B (it) 1974-04-10

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