GB767656A - Improvements in or relating to axial-flow fluid machines such as turbines and compressors - Google Patents

Improvements in or relating to axial-flow fluid machines such as turbines and compressors

Info

Publication number
GB767656A
GB767656A GB3144253A GB3144253A GB767656A GB 767656 A GB767656 A GB 767656A GB 3144253 A GB3144253 A GB 3144253A GB 3144253 A GB3144253 A GB 3144253A GB 767656 A GB767656 A GB 767656A
Authority
GB
United Kingdom
Prior art keywords
radially
axial
extending
rotor blades
ribs
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
GB3144253A
Inventor
John Gregory Keenan
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 PLC
Original Assignee
Rolls Royce PLC
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
Priority to BE533093D priority Critical patent/BE533093A/xx
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3144253A priority patent/GB767656A/en
Priority to FR1111037D priority patent/FR1111037A/en
Publication of GB767656A publication Critical patent/GB767656A/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
    • 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

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)

Abstract

767,656. Axial-flow turbines and compressors. ROLLS-ROYCE. Ltd. Oct. 22, 1954 [Nov. 12,1953], No. 31442/53. Class 110 (3). In an axial-flow turbine or compressor for example of a gas turbine engine, in which the rotor blades have at their radially outer ends. blade tip shrouds, upstanding circumferential ribs are provided on the outer surfaces of the shrouds, each rib having a radially-extending surface thereon. The adjacent stator structure is formed with radially.inwardly-facing circumferentially-extending grooves, each groove receiving one of the ribs and having a side wall affording a radially-extending surface which is spaced from the radially-extending surface of the associated rib to provide an axial gassealing clearance therebetween. Adjacent stator structure has radial clearances from the rotor blades greater than the said axial gas-sealing clearance. The rotor blades 11a have a shroud ring 12a, the shroud being formed with two circumferential ribs 46 which have radiallyextending surfaces 47. A stator element 17 secured to the casing section 14 is formed with grooves 48 which provide radially-extending surfaces 49 which co-operate with the surfaces 47 on the ribs to provide axial gas-sealing clearances. The upstream edge of the shroud 12a is also formed with a radially-extending surface 50 which co-operates with the surface 51 on the nozzle guide vane platform 19a to provide a third axial gas-sealing clearance. The nozzle guide vane platforms such as 19a have axially- and radially-extending surfaces by which they are located in the casing structure which comprises sections 13, 14, 15, 16. The radially-inwardly-facing surfaces of the shrouds of the row of rotor blades affords with the adjacent stator structure a substantially continuous bounding surface for the working fluid.
GB3144253A 1953-11-12 1953-11-12 Improvements in or relating to axial-flow fluid machines such as turbines and compressors Expired GB767656A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
BE533093D BE533093A (en) 1953-11-12
GB3144253A GB767656A (en) 1953-11-12 1953-11-12 Improvements in or relating to axial-flow fluid machines such as turbines and compressors
FR1111037D FR1111037A (en) 1953-11-12 1954-10-28 Improvements to axial flow fluid machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3144253A GB767656A (en) 1953-11-12 1953-11-12 Improvements in or relating to axial-flow fluid machines such as turbines and compressors

Publications (1)

Publication Number Publication Date
GB767656A true GB767656A (en) 1957-02-06

Family

ID=10323152

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3144253A Expired GB767656A (en) 1953-11-12 1953-11-12 Improvements in or relating to axial-flow fluid machines such as turbines and compressors

Country Status (3)

Country Link
BE (1) BE533093A (en)
FR (1) FR1111037A (en)
GB (1) GB767656A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916332A (en) * 1958-09-08 1959-12-08 Vladimir H Pavlecka Aerostatic bearings with fluid-dynamic seals
US4050845A (en) * 1975-09-30 1977-09-27 Kraftwerk Union Aktiengesellschaft Device for stabilizing the position of rotors of large steam turbines
FR2550275A1 (en) * 1983-08-01 1985-02-08 United Technologies Corp
US4662820A (en) * 1984-07-10 1987-05-05 Hitachi, Ltd. Turbine stage structure
EP0903468A1 (en) * 1997-09-19 1999-03-24 Asea Brown Boveri AG Shroud for an axial turbine
EP1967700A3 (en) * 2007-03-05 2010-05-05 United Technologies Corporation Labyrinth seal having canted pockets and knife edges, and gas turbine engine with such a seal
EP1930551A3 (en) * 2006-11-29 2010-05-12 United Technologies Corporation Seal with concave recess and corresponding gas turbine engine
DE102009042857A1 (en) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with shroud labyrinth seal
US20130084168A1 (en) * 2011-09-29 2013-04-04 General Electric Company Clearance flow control assembly having rail member
CN104912604A (en) * 2015-06-01 2015-09-16 西安交通大学 Anti-rotation plate structure with rotation stopping and vibration restraining actions
WO2018184788A1 (en) * 2017-04-05 2018-10-11 Siemens Aktiengesellschaft Method for sealing an annular gap in a turbine, and turbine
CN108708771A (en) * 2018-04-28 2018-10-26 北京航天动力研究所 A kind of high-molecular organic material dynamic sealing device for cryogenic turbo

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5501573A (en) * 1993-01-29 1996-03-26 Steam Specialties, Inc. Segmented seal assembly and method for retrofitting the same to turbines and the like
FR3065482B1 (en) * 2017-04-20 2019-07-05 Safran Aircraft Engines SEAL RING MEMBER FOR TURBINE COMPRISING A CAVITY INCLINED IN ABRADABLE MATERIAL

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916332A (en) * 1958-09-08 1959-12-08 Vladimir H Pavlecka Aerostatic bearings with fluid-dynamic seals
US4050845A (en) * 1975-09-30 1977-09-27 Kraftwerk Union Aktiengesellschaft Device for stabilizing the position of rotors of large steam turbines
FR2550275A1 (en) * 1983-08-01 1985-02-08 United Technologies Corp
US4662820A (en) * 1984-07-10 1987-05-05 Hitachi, Ltd. Turbine stage structure
EP0903468A1 (en) * 1997-09-19 1999-03-24 Asea Brown Boveri AG Shroud for an axial turbine
JPH11148308A (en) * 1997-09-19 1999-06-02 Asea Brown Boveri Ag Shroud band for axial-flow turbine
US6102655A (en) * 1997-09-19 2000-08-15 Asea Brown Boveri Ag Shroud band for an axial-flow turbine
EP1930551A3 (en) * 2006-11-29 2010-05-12 United Technologies Corporation Seal with concave recess and corresponding gas turbine engine
EP1967700A3 (en) * 2007-03-05 2010-05-05 United Technologies Corporation Labyrinth seal having canted pockets and knife edges, and gas turbine engine with such a seal
US8167547B2 (en) 2007-03-05 2012-05-01 United Technologies Corporation Gas turbine engine with canted pocket and canted knife edge seal
DE102009042857A1 (en) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with shroud labyrinth seal
EP2302174A3 (en) * 2009-09-24 2014-01-22 Rolls-Royce Deutschland Ltd & Co KG Gas turbine shroud labyrinth seal
US20130084168A1 (en) * 2011-09-29 2013-04-04 General Electric Company Clearance flow control assembly having rail member
US8807927B2 (en) * 2011-09-29 2014-08-19 General Electric Company Clearance flow control assembly having rail member
CN104912604A (en) * 2015-06-01 2015-09-16 西安交通大学 Anti-rotation plate structure with rotation stopping and vibration restraining actions
WO2018184788A1 (en) * 2017-04-05 2018-10-11 Siemens Aktiengesellschaft Method for sealing an annular gap in a turbine, and turbine
US11753938B2 (en) 2017-04-05 2023-09-12 Siemens Energy Global GmbH & Co. KG Method for sealing an annular gap in a turbine, and turbine
CN108708771A (en) * 2018-04-28 2018-10-26 北京航天动力研究所 A kind of high-molecular organic material dynamic sealing device for cryogenic turbo

Also Published As

Publication number Publication date
BE533093A (en) 1954-11-30
FR1111037A (en) 1956-02-21

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