GB617474A - Improvements relating to gas-turbine engines - Google Patents

Improvements relating to gas-turbine engines

Info

Publication number
GB617474A
GB617474A GB29429/46A GB2942946A GB617474A GB 617474 A GB617474 A GB 617474A GB 29429/46 A GB29429/46 A GB 29429/46A GB 2942946 A GB2942946 A GB 2942946A GB 617474 A GB617474 A GB 617474A
Authority
GB
United Kingdom
Prior art keywords
disc
discs
flange
bolt
shaped member
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
GB29429/46A
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.)
PHILLIP EDGAR HUNTER
Original Assignee
PHILLIP EDGAR HUNTER
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 PHILLIP EDGAR HUNTER filed Critical PHILLIP EDGAR HUNTER
Priority to GB29429/46A priority Critical patent/GB617474A/en
Publication of GB617474A publication Critical patent/GB617474A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Abstract

617,474. Coupling turbine discs. JUDSON, C. A., READ, J. R., and HUNTER, P. E. Oct. 2, 1946, No. 29429. [Class 80 (ii)] [Also in Groups XXV and XXVI] In a turbine rotor assembly comprising two or more axially-spaced discs, at least one disc is attached to an adjacent disc by a bolt member which passes through a central bore in one disc and engages a threaded part on the other and abutment means are provided to axially space the discs at a radius greater than that of the bolt member. The abutment means may be a separate spacer ring. A second abutment at a smaller radius than the first may also be provided. The turbine disc 20, Fig. 2, is attached to the turbine disc 19 by a bolt member 34 which engages a nut 33 spigoted and bolted to the flange 32 of the disc 19. The discs are spaced axially by a T-shaped member 35 which encircles the bolt member. A spigot 41 on the disc 20 is received in a recess of the nut 33 and abuts against a washer 42 accommodated in the bottom of the recess. This forms a second abutment between the two discs at a smaller radius than the first and by means of selective assembly of the T-shaped member 35 and the washer 42 it is possible to adjust the load between the discs and the member 35. A ring 44 bolted to the flange 46 has an axial flange formed with teeth which engage corresponding teeth on the bolt head 43 to prevent the bolt 34 slacking off. The leg of the T-shaped member 35 is formed at its inner radius with splines 38 which engage corresponding formations on the flanges 32 and 39 of the discs to assist in the transmission of torque from one disc to the other. The peripheral flange of the T-shaped member 35 may be frusto-conical in form and have its outer surface stepped to co-operate with a similarly shaped flange 37 on the sealing diaphragm between the discs. The T-shaped member is located on the nut 33 by lugs 40. The disc 19 is bolted to the shaft 12 and a sleeve 29 on which the bearing 30 is mounted. The sleeve 29 is formed with a flange in which are cut splines which engage splines cut in the flanges 27, 28 of the disc 19 and shaft 12. The bolt member may be hollow and used as a passage for the supply of cooling air as described and claimed in Specification 617,473, [Group XXVI]. According to the Provisional Specification the head of the bolt may be provided with a flange drilled with a circular series of holes which are used in conjunction with a series of holes in a flange of one of the discs to prevent rotation of the bolt. The holes are drilled so as to give a vernier adjustment.
GB29429/46A 1946-10-02 1946-10-02 Improvements relating to gas-turbine engines Expired GB617474A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB29429/46A GB617474A (en) 1946-10-02 1946-10-02 Improvements relating to gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29429/46A GB617474A (en) 1946-10-02 1946-10-02 Improvements relating to gas-turbine engines

Publications (1)

Publication Number Publication Date
GB617474A true GB617474A (en) 1949-02-07

Family

ID=10291423

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29429/46A Expired GB617474A (en) 1946-10-02 1946-10-02 Improvements relating to gas-turbine engines

Country Status (1)

Country Link
GB (1) GB617474A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2640315A (en) * 1949-06-28 1953-06-02 A V Roe Canada Ltd Gas turbine starter mounting
US2712729A (en) * 1951-12-06 1955-07-12 Ruston & Hornsby Ltd Cooling systems of gas-turbines
US2759700A (en) * 1950-02-04 1956-08-21 Gen Motors Corp Bearing cooling system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2640315A (en) * 1949-06-28 1953-06-02 A V Roe Canada Ltd Gas turbine starter mounting
US2759700A (en) * 1950-02-04 1956-08-21 Gen Motors Corp Bearing cooling system
US2712729A (en) * 1951-12-06 1955-07-12 Ruston & Hornsby Ltd Cooling systems of gas-turbines

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