GB1307140A - Locking devices for securing concentric cylindrical parts - Google Patents

Locking devices for securing concentric cylindrical parts

Info

Publication number
GB1307140A
GB1307140A GB4322471A GB4322471A GB1307140A GB 1307140 A GB1307140 A GB 1307140A GB 4322471 A GB4322471 A GB 4322471A GB 4322471 A GB4322471 A GB 4322471A GB 1307140 A GB1307140 A GB 1307140A
Authority
GB
United Kingdom
Prior art keywords
shroud ring
disc
flange
recess
casing
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
Application number
GB4322471A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation Co
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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1307140A publication Critical patent/GB1307140A/en
Expired legal-status Critical Current

Links

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical

Landscapes

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

Abstract

1307140 Cotters GENERAL MOTORS CORP 16 Sept 1971 [21 Sept 1970] 43224/71 Heading F2H [Also in Divisions E2 and F1] The invention relates to a locking device and is described with reference to its application for securing turbine stator casing parts together. The turbine casing comprises upstream, intermediate and downstream parts 14, 12, 10, shroud ring membsrs 36, 34, 32, 30 being located within the parts 14, 12, 10, the shroud rings being located by tongue and groove connections. The casing part 12 is formed at its upstream end with a flange 68 which is secured to a flange on the upstream casing part 14 by bolts 18. The shroud ring 34 is formed with a flange 60 which is received within an annular recess in the casing part 14. A series of part-circular recesses 78 are formed in the upstream face of the flange 68 and an annular groove 80 is formed in the flange 60 of the shroud ring such that the recesses 78 are aligned with the recess 80. A partcircular disc 70 is disposed in each recess 78, the disc having a circular portion 72 and a chord portion 74, a semi-circular recess 76 being formed in the chord portion; the disc is formed with a screw-driver slot 82 whereby the disc may be rotated. In the unlocked position of the disc shown at the right side of Fig. 3 the chord portion 74 is adjacent the shroud ring 34. Upon rotating the disc to the locked position shown at the left side of Fig. 3, the circular portion 72 engages within the annular recess 80 in the shroud ring 34 whereby the shroud ring is located axially of the stator casing. The bolt 18 is entered through the flanges and engages the recess 76 in the locking disc 70 whereby the disc is locked against rotation. In place of an annular recess 80 in the shroud ring 34, part-circular recesses only may be provided whereby the shroud ring is prevented from angular movement relative to the outer casing. In a further embodiment the recesses such as 80 in the flange 60 of the shroud ring are open at their upstream sides so that the shroud ring is constrained against movement relative to the stator casing in an upstream direction only.
GB4322471A 1970-09-21 1971-09-16 Locking devices for securing concentric cylindrical parts Expired GB1307140A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US7400870A 1970-09-21 1970-09-21

Publications (1)

Publication Number Publication Date
GB1307140A true GB1307140A (en) 1973-02-14

Family

ID=22117141

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4322471A Expired GB1307140A (en) 1970-09-21 1971-09-16 Locking devices for securing concentric cylindrical parts

Country Status (3)

Country Link
US (1) US3644057A (en)
CA (1) CA935381A (en)
GB (1) GB1307140A (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3990807A (en) * 1974-12-23 1976-11-09 United Technologies Corporation Thermal response shroud for rotating body
US4074914A (en) * 1975-07-28 1978-02-21 United Technologies Corporation High pressure lightweight flanges
US4053189A (en) * 1976-06-17 1977-10-11 United Technologies Corporation Turbine construction
US4525997A (en) * 1983-08-01 1985-07-02 United Technologies Corporation Stator assembly for bounding the flow path of a gas turbine engine
US4621976A (en) * 1985-04-23 1986-11-11 United Technologies Corporation Integrally cast vane and shroud stator with damper
US4687413A (en) * 1985-07-31 1987-08-18 United Technologies Corporation Gas turbine engine assembly
US5141394A (en) * 1990-10-10 1992-08-25 Westinghouse Electric Corp. Apparatus and method for supporting a vane segment in a gas turbine
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
FR2761119B1 (en) * 1997-03-20 1999-04-30 Snecma TURBOMACHINE COMPRESSOR STATOR
FR2875534B1 (en) 2004-09-21 2006-12-22 Snecma Moteurs Sa TURBINE MODULE FOR A GAS TURBINE ENGINE WITH ROTOR COMPRISING A MONOBLOC BODY
FR2875535B1 (en) * 2004-09-21 2009-10-30 Snecma Moteurs Sa TURBINE MODULE FOR GAS TURBINE ENGINE
US9133732B2 (en) 2010-05-27 2015-09-15 Siemens Energy, Inc. Anti-rotation pin retention system
US10890085B2 (en) * 2018-09-17 2021-01-12 Rolls-Royce Corporation Anti-rotation feature

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR961133A (en) * 1947-02-17 1950-05-05
US2722373A (en) * 1951-02-06 1955-11-01 United Aircraft Corp Compressor casing and stator assembly
US2766693A (en) * 1952-11-05 1956-10-16 Sundstrand Machine Tool Co Pump
US2915281A (en) * 1957-06-03 1959-12-01 Gen Electric Stator vane locking key
US3069135A (en) * 1957-10-03 1962-12-18 Gen Motors Corp Vane ring assembly
US3295751A (en) * 1965-04-21 1967-01-03 United Aircraft Corp Compressor stator shroud arrangement

Also Published As

Publication number Publication date
US3644057A (en) 1972-02-22
CA935381A (en) 1973-10-16

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees