GB1335553A - Bladed rotor for a gas turbine engine - Google Patents

Bladed rotor for a gas turbine engine

Info

Publication number
GB1335553A
GB1335553A GB1754670A GB1335553DA GB1335553A GB 1335553 A GB1335553 A GB 1335553A GB 1754670 A GB1754670 A GB 1754670A GB 1335553D A GB1335553D A GB 1335553DA GB 1335553 A GB1335553 A GB 1335553A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
rotor
blades
turbine engine
ties
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
GB1754670A
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Publication of GB1335553A publication Critical patent/GB1335553A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Abstract

1335553 Turbine blades DEFENCE SECRETARY OF STATE FOR 19 April 1971 [13 April 1970] 17546/70 Heading FIT A gas turbine rotor comprises blades 10 connected by ties 13 each of which is formed from a Z-shaped piece of sheet metal and has a curved metal strip portion 14 convex towards the axis of the rotor. The metal strips have a substantially catenary shape so that in operation centrifugal forces cause the ties to be under mainly compressive stress. The limbs of the 'Z' are bent up to form lugs 15 for attachment to the rotor blades.
GB1754670A 1970-04-13 1971-04-19 Bladed rotor for a gas turbine engine Expired GB1335553A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1754670 1970-04-13

Publications (1)

Publication Number Publication Date
GB1335553A true GB1335553A (en) 1973-10-31

Family

ID=10097090

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1754670A Expired GB1335553A (en) 1970-04-13 1971-04-19 Bladed rotor for a gas turbine engine

Country Status (5)

Country Link
US (1) US3708244A (en)
DE (1) DE2117387A1 (en)
FR (1) FR2089567A5 (en)
GB (1) GB1335553A (en)
IT (1) IT942542B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251897A (en) * 1991-01-15 1992-07-22 Rolls Royce Plc Bladed rotor

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4407634A (en) * 1981-09-08 1983-10-04 Northern Engineering Industries Plc Axial-flow steam turbine wheel
CH667493A5 (en) * 1985-05-31 1988-10-14 Bbc Brown Boveri & Cie DAMPING ELEMENT FOR DETACHED TURBO MACHINE BLADES.
US4798519A (en) * 1987-08-24 1989-01-17 United Technologies Corporation Compressor part span shroud
US5984638A (en) * 1994-08-12 1999-11-16 Elliott Turbomachinery Co., Inc. Turbomachine radial impeller vibration constraining and damping mechanism
JP3555097B2 (en) * 1995-09-28 2004-08-18 矢崎総業株式会社 Electrode materials and secondary batteries
GB2441543B (en) * 2006-09-07 2008-07-23 Rolls Royce Plc An array of components
US8647051B2 (en) * 2009-09-16 2014-02-11 The Bergquist Torrington Company High efficiency low-profile centrifugal fan
US8540488B2 (en) * 2009-12-14 2013-09-24 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US8616848B2 (en) * 2009-12-14 2013-12-31 Siemens Energy, Inc. Turbine blade damping device with controlled loading
USRE45690E1 (en) 2009-12-14 2015-09-29 Siemens Energy, Inc. Turbine blade damping device with controlled loading
TWI418708B (en) * 2011-03-25 2013-12-11 Delta Electronics Inc Impeller structure
US20160040537A1 (en) * 2014-08-07 2016-02-11 General Electric Company Turbine blade mid-span shroud assembly
US11913355B2 (en) * 2022-02-14 2024-02-27 General Electric Company Part-span shrouds for pitch controlled aircrafts

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US937006A (en) * 1906-03-03 1909-10-12 Allis Chalmers Steam-turbine.
GB315722A (en) * 1928-07-16 1930-02-27 The British Thomson-Houston Company Limited
DE563458C (en) * 1929-02-10 1932-11-05 Siemens Schuckertwerke Akt Ges Stiffening of steam turbine blades
DE818806C (en) * 1949-02-17 1951-10-29 Escher Wyss Ag Blading on rotors of axially flowed through, strongly twisted blades having centrifugal machines, in particular steam, gas turbines and compressors
GB770528A (en) * 1954-02-05 1957-03-20 Gen Electric Co Ltd Improvements in or relating to steam turbines
GB910239A (en) * 1959-12-07 1962-11-14 Gen Electric Co Ltd Improvements in or relating to steam turbines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251897A (en) * 1991-01-15 1992-07-22 Rolls Royce Plc Bladed rotor
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor

Also Published As

Publication number Publication date
US3708244A (en) 1973-01-02
DE2117387A1 (en) 1971-11-04
IT942542B (en) 1973-04-02
FR2089567A5 (en) 1972-01-07

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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