GB722514A - Improvements relating to axial-flow turbine and compressor rotors - Google Patents

Improvements relating to axial-flow turbine and compressor rotors

Info

Publication number
GB722514A
GB722514A GB16084/51A GB1608451A GB722514A GB 722514 A GB722514 A GB 722514A GB 16084/51 A GB16084/51 A GB 16084/51A GB 1608451 A GB1608451 A GB 1608451A GB 722514 A GB722514 A GB 722514A
Authority
GB
United Kingdom
Prior art keywords
blade
root
coating
turbine
filling
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
GB16084/51A
Inventor
Cyril Armer
Nelson Hector Kent
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
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB16084/51A priority Critical patent/GB722514A/en
Publication of GB722514A publication Critical patent/GB722514A/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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling
    • F01D5/183—Blade walls being porous
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

722,514. Turbines and compressors. ROLLSROYCE, Ltd. Aug. 27, 1952 [July 6, 1951], No. 16084/51. Classes 110 (1) and 110 (3). A rotor assembly for an axialflow turbine or compressor comprises blading of porous material mounted on a disc or drum and means for supplying liquid to the root ends of the blades, at least that part of the surface of each blade adjacent the root end being rendered impervious to liquid by a metallic filling or coating applied during the manufacture of the blade. Each blade 10 has a radially-inwardly-facing cup-shaped recess 14 in the blade root, an open-ended thimble member 15 being fitted therein. The whole of the working surface of the blade and root portion is made impervious by a filling or coating 10b. In another embodiment, the tip portion of a blade is uncoated and the area of the working surface which is coated increases towards the root end. The porous blade may be formed from sintered metal powder, such as stainless steel, and the coating may be sprayed or electrolytically deposited. The metal of the filling or coating may have a melting point near to the maximum permissible blade temperature. The invention is applicable where it is desired to add fluid for cooling the blades, for anti-icing purposes, for example, where water-methanol is introduced into a compressor duct, for increasing the power of a gas-turbine aircraft-propulsion engine by introducing an additional liquid such as water methanol, or for reheating the working medium passing through a turbine by addition of fuel. The rotor construction forms the subject of Specification 722,515.
GB16084/51A 1952-08-27 1952-08-27 Improvements relating to axial-flow turbine and compressor rotors Expired GB722514A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB16084/51A GB722514A (en) 1952-08-27 1952-08-27 Improvements relating to axial-flow turbine and compressor rotors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB16084/51A GB722514A (en) 1952-08-27 1952-08-27 Improvements relating to axial-flow turbine and compressor rotors

Publications (1)

Publication Number Publication Date
GB722514A true GB722514A (en) 1955-01-26

Family

ID=10070889

Family Applications (1)

Application Number Title Priority Date Filing Date
GB16084/51A Expired GB722514A (en) 1952-08-27 1952-08-27 Improvements relating to axial-flow turbine and compressor rotors

Country Status (1)

Country Link
GB (1) GB722514A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3402914A (en) * 1965-02-10 1968-09-24 Curtiss Wright Corp Method of controlling the permeability of a porous material, and turbine blade formed thereby
US3647316A (en) * 1970-04-28 1972-03-07 Curtiss Wright Corp Variable permeability and oxidation-resistant airfoil
US3778188A (en) * 1972-09-11 1973-12-11 Gen Motors Corp Cooled turbine rotor and its manufacture

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3402914A (en) * 1965-02-10 1968-09-24 Curtiss Wright Corp Method of controlling the permeability of a porous material, and turbine blade formed thereby
US3647316A (en) * 1970-04-28 1972-03-07 Curtiss Wright Corp Variable permeability and oxidation-resistant airfoil
US3778188A (en) * 1972-09-11 1973-12-11 Gen Motors Corp Cooled turbine rotor and its manufacture

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