GB761829A - Stator ring assembly for a rotary bladed fluid flow machine - Google Patents

Stator ring assembly for a rotary bladed fluid flow machine

Info

Publication number
GB761829A
GB761829A GB30473/54A GB3047354A GB761829A GB 761829 A GB761829 A GB 761829A GB 30473/54 A GB30473/54 A GB 30473/54A GB 3047354 A GB3047354 A GB 3047354A GB 761829 A GB761829 A GB 761829A
Authority
GB
United Kingdom
Prior art keywords
segments
outer ring
nuts
nut
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
Application number
GB30473/54A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB761829A publication Critical patent/GB761829A/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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing

Landscapes

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

Abstract

761,829. Turbine and compressor casings. KELK, G. F., and KLOMPAS, N. Oct. 22, 1954 [Feb. 4, 1954], No. 30473/54. Classes 110 (1) and 110 (3). A stator ring assembly for a turbine or compressor comprises an outer ring 20, an inner ring comprising a plurality of arcuate segments 28 disposed within the outer ring and radially spaced therefrom, and a plurality of supporting means supporting the segments from the outer ring, the supporting means bridging the gaps between adjacent ends of adjacent segments. Each supporting means is adjustable independently of the others relative to the outer ring so that the radial positions of the segments relative to the outer ring may be varied. In Fig. 4, the segments 28 have strengthening plates 28a welded thereto, the plates being pressed at 28c for rigidity. The outer ring 20 is formed with holes 20d in which bolt-guiding sleeves 22 are secured by locknuts 23. T-headed bolts 29. pass through the sleeves and are adjustable radially by means of castellated nuts 31 which are prevented from axial movement by means of U-shaped clips 32 which engage slots 33 formed in the sleeve 22 and a circumferential groove 34 formed in each nut 31. The heads of the T-bolts are grooved to form an H-section, the recesses of which receive the adjacent ends of the strengthening plates 28a so that adjustment of the nuts 31 adjusts the radial positions of the segments 28. The nuts 31 are locked by means of cotter-pins 35 passed through holes 29a in the bolts. The lock-nuts 23 also support retaining plates 24 which press insulation 25 against the inner surface of the outer shroud ring. The adjacent U-clips 32 are wired together. In a second embodiment, Fig. 5, each adjusting nut 31<SP>1</SP> is formed with a frusto-conical portion 31a<SP>1</SP> which engages a conical recess 22b<SP>1</SP> in the bolt-guiding sleeve 22<SP>1</SP>. A nut 38 screwed on the sleeve 22<SP>1</SP> locks the parts together, the lock-nut being secured by wire 39 to a tab 40a.
GB30473/54A 1954-02-04 1954-10-22 Stator ring assembly for a rotary bladed fluid flow machine Expired GB761829A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US761829XA 1954-02-04 1954-02-04

Publications (1)

Publication Number Publication Date
GB761829A true GB761829A (en) 1956-11-21

Family

ID=22130450

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30473/54A Expired GB761829A (en) 1954-02-04 1954-10-22 Stator ring assembly for a rotary bladed fluid flow machine

Country Status (1)

Country Link
GB (1) GB761829A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2228539A (en) * 1989-02-23 1990-08-29 United Technologies Corp Stator assembly for a rotary machine
GB2238354A (en) * 1989-11-22 1991-05-29 Gen Electric Blade tip clearance control apparatus
US5056988A (en) * 1990-02-12 1991-10-15 General Electric Company Blade tip clearance control apparatus using shroud segment position modulation
GB2261708A (en) * 1991-11-20 1993-05-26 Snecma Turbo-shaft engine casing and blade mounting
GB2265184A (en) * 1992-03-10 1993-09-22 Rolls Royce Plc Gas turbine engine support structure.

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2228539A (en) * 1989-02-23 1990-08-29 United Technologies Corp Stator assembly for a rotary machine
GB2228539B (en) * 1989-02-23 1993-09-01 United Technologies Corp Casing for a rotary machine
GB2238354A (en) * 1989-11-22 1991-05-29 Gen Electric Blade tip clearance control apparatus
US5056988A (en) * 1990-02-12 1991-10-15 General Electric Company Blade tip clearance control apparatus using shroud segment position modulation
GB2261708A (en) * 1991-11-20 1993-05-26 Snecma Turbo-shaft engine casing and blade mounting
GB2261708B (en) * 1991-11-20 1995-01-25 Snecma Turbo-shaft engine stator
GB2265184A (en) * 1992-03-10 1993-09-22 Rolls Royce Plc Gas turbine engine support structure.
US5288204A (en) * 1992-03-10 1994-02-22 Rolls-Royce Plc Gas turbine engine support structure
GB2265184B (en) * 1992-03-10 1995-01-25 Rolls Royce Plc Gas turbine engine support structure

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