GB791568A - Improvements in axial flow compressors - Google Patents

Improvements in axial flow compressors

Info

Publication number
GB791568A
GB791568A GB931856A GB931856A GB791568A GB 791568 A GB791568 A GB 791568A GB 931856 A GB931856 A GB 931856A GB 931856 A GB931856 A GB 931856A GB 791568 A GB791568 A GB 791568A
Authority
GB
United Kingdom
Prior art keywords
per cent
coating
powdered
finely
formaldehyde
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
GB931856A
Inventor
Frederick R Short
Robert B Koschmann
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
Priority to US339012A priority Critical patent/US2962809A/en
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Priority to GB931856A priority patent/GB791568A/en
Priority to CH344168D priority patent/CH344168A/en
Priority to FR1150778D priority patent/FR1150778A/en
Publication of GB791568A publication Critical patent/GB791568A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material

Abstract

In an axial-flow compressor, the portions of the housing adjacent the paths of the rotor blade tips are coated with an abradable skin that can be machined by the blade tips in motion. The coating may be applied to the housing by brushing, spraying, or by the use of a roller or spreader. Alternatively, it may be in sheet or tape form bonded to the housing. The coating is heated at a temperature rising from 100 DEG F. to 500 DEG F. in hourly steps of 100 degrees to harden it, and is then machined to a thickness of, say, 0.01 to 0.03 inches. The tips of the rotor blades can, if necessary, machine the coating to establish a minimum working clearance. The coating may comprise a mixture of a filler such as powdered graphite or finely-divided asbestos, or both, with a heat hardenable silicone resin, a thermosetting resin, e.g. phenol-formaldehyde, urea-formaldehyde, melamine-formaldehyde and certain fluoro-carbon resins, or a heat hardenable material such as sodium silicate, with the addition of a volatile solvent or diluent. Other fillers which may be used are glass fibre, silica flour or other ceramic material, powdered spent catalyst or powdered metals such as aluminium, antimony, tin and lead. The solvent or diluent may include secondary butyl acetate, mineral spirits, xylene, toluene or other liquid hydrocarbons. Plasticizers, such as various phthalates and glycol esters, may be included to improve the flexibility of the coating at low temperatures.ALSO:A coating composition comprises a heathardenable silicone resin or a thermosetting resin such as phenol formaldehyde, urea formaldehyde, melamine formaldehyde, or a fluorocarbon resin, with a filler such as powdered graphite, finely-divided asbestos, glass fibre, silica flour or other ceramic material, powdered spent catalyst, tin and lead, and a solvent or diluent such as secondary butyl acetate, mineral spirits, xylene, toluene or other liquid hydrocarbons. Plasticizers, such as various phthalates and glycol esters, may be included to improve the flexibility of the coating at low temperatures. After application, the coating is cured by heating it at a temperature rising from 100 to 500 DEG F. in hourly steps of 100 degrees. In general, the composition can be made by adding up to 2 gm. of powdered graphite or asbestos or both per c.c. of a mixture comprising 15-45 per cent of one or more silicone resins, up to 75 per cent of volatile solvent or diluent or both, and, optionally, 7-12 per cent of finely-divided metallic powder. A preferred composition comprises 7-45 per cent of heat-hardenable silicone resin, 15-55 per cent of powdered graphite or finely-divided asbestos or both, up to 10 per cent of finely-divided aluminium or other metal, and up to 65 per cent of volatile matter. The composition can be made by adding about 1 gm. of powdered graphite or finely-divided asbestos per c.c. of a silicone resin paint. Alternatively, 0.25 gm. of powdered graphite is added per c.c. of a liquid mixture comprising 7 per cent of powdered aluminium, 40 per cent of a heat-hardenable silicone resin, and 53 per cent of toluene.
GB931856A 1953-02-26 1956-03-26 Improvements in axial flow compressors Expired GB791568A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US339012A US2962809A (en) 1953-02-26 1953-02-26 Method of making a compressor seal
GB931856A GB791568A (en) 1956-03-26 1956-03-26 Improvements in axial flow compressors
CH344168D CH344168A (en) 1956-03-26 1956-04-06 Method for applying a coating, which serves to reduce the rotor blade tip clearance, on the inside of the housing of axial compressors, and coating produced according to this method
FR1150778D FR1150778A (en) 1956-03-26 1956-04-11 Axial compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB931856A GB791568A (en) 1956-03-26 1956-03-26 Improvements in axial flow compressors

Publications (1)

Publication Number Publication Date
GB791568A true GB791568A (en) 1958-03-05

Family

ID=9869665

Family Applications (1)

Application Number Title Priority Date Filing Date
GB931856A Expired GB791568A (en) 1953-02-26 1956-03-26 Improvements in axial flow compressors

Country Status (3)

Country Link
CH (1) CH344168A (en)
FR (1) FR1150778A (en)
GB (1) GB791568A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3039737A (en) * 1959-04-13 1962-06-19 Int Harvester Co Device for controlling clearance between rotor and shroud of a turbine
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
US3083529A (en) * 1959-03-24 1963-04-02 Charles W F Hemilton Hydraulic jet propulsion apparatus for water-borne craft
US3092306A (en) * 1958-04-28 1963-06-04 Gen Motors Corp Abradable protective coating for compressor casings
US3173605A (en) * 1963-06-21 1965-03-16 Rotron Mfg Co Fan housing
EP0722989A1 (en) * 1995-01-17 1996-07-24 Dow Corning Corporation Organosiloxane compositions yielding machinable erosion resistant elastomers
US20110002779A1 (en) * 2008-12-24 2011-01-06 Laurent Schuster Method for Manufacturing by Molding a Machine Structural Element Having an Abradable Surface, and Structural Element
EP1975271A3 (en) * 2007-03-24 2011-05-18 Rolls-Royce plc A method of repairing a damaged abradable coating
WO2013075954A1 (en) * 2011-11-25 2013-05-30 Rolls-Royce Plc Abradable liner for a gas turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2112878B (en) * 1981-12-28 1985-12-04 United Technologies Corp Air seal for compressor stator
DE3316535A1 (en) * 1983-05-06 1984-11-08 MTU Motoren- und Turbinen-Union München GmbH, 8000 München TURBO COMPRESSOR WITH INLET COVER

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3092306A (en) * 1958-04-28 1963-06-04 Gen Motors Corp Abradable protective coating for compressor casings
US3083529A (en) * 1959-03-24 1963-04-02 Charles W F Hemilton Hydraulic jet propulsion apparatus for water-borne craft
US3039737A (en) * 1959-04-13 1962-06-19 Int Harvester Co Device for controlling clearance between rotor and shroud of a turbine
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
US3173605A (en) * 1963-06-21 1965-03-16 Rotron Mfg Co Fan housing
EP0722989A1 (en) * 1995-01-17 1996-07-24 Dow Corning Corporation Organosiloxane compositions yielding machinable erosion resistant elastomers
EP1975271A3 (en) * 2007-03-24 2011-05-18 Rolls-Royce plc A method of repairing a damaged abradable coating
US8563080B2 (en) 2007-03-24 2013-10-22 Rolls-Royce Plc Method of repairing a damaged abradable coating
US20110002779A1 (en) * 2008-12-24 2011-01-06 Laurent Schuster Method for Manufacturing by Molding a Machine Structural Element Having an Abradable Surface, and Structural Element
US8491258B2 (en) * 2008-12-24 2013-07-23 Techspace Aero S.A. Method for manufacturing by molding a machine structural element having an abradable surface, and structural element
WO2013075954A1 (en) * 2011-11-25 2013-05-30 Rolls-Royce Plc Abradable liner for a gas turbine

Also Published As

Publication number Publication date
FR1150778A (en) 1958-01-17
CH344168A (en) 1960-01-31

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