GB703489A - Improvements in or relating to axial-flow compressor or turbine rotors - Google Patents

Improvements in or relating to axial-flow compressor or turbine rotors

Info

Publication number
GB703489A
GB703489A GB4213/51A GB421351A GB703489A GB 703489 A GB703489 A GB 703489A GB 4213/51 A GB4213/51 A GB 4213/51A GB 421351 A GB421351 A GB 421351A GB 703489 A GB703489 A GB 703489A
Authority
GB
United Kingdom
Prior art keywords
sleeve
flanges
discs
axial
flow compressor
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
GB4213/51A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB703489A publication Critical patent/GB703489A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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

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

703,489. Turbine and compressor rotors. UNITED AIRCRAFT CORPORATION. Feb. 21, 1951 [March 23, 1950], No. 4213/51. Class 110 (3) An axial-flow compressor or turbine rotor comprises a plurality of bladed discs 2, a series of bolts 14 extending therethrough and arranged in a ring surrounding and spaced from the axis of rotation of said discs, a sleeve 22 extending between adjacent discs and surrounding the ring of bolts and a plurality of tubes 28 carried by the sleeve and positioned for spacing adjacent discs. The tubes 28 are preferably a loose fit in one of the flanges 25 of the sleeve 22 and a press fit in the other flange thereof. The sleeve is slightly shorter than the tube. When the disc is liable to be subjected to a greater thermal expansion than that of the sleeve, the disc is provided with flanges which support the inner edges of the flanges 25 of the sleeve. Specification 571,205 is referred to.
GB4213/51A 1950-03-23 1951-02-21 Improvements in or relating to axial-flow compressor or turbine rotors Expired GB703489A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US703489XA 1950-03-23 1950-03-23

Publications (1)

Publication Number Publication Date
GB703489A true GB703489A (en) 1954-02-03

Family

ID=22094759

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4213/51A Expired GB703489A (en) 1950-03-23 1951-02-21 Improvements in or relating to axial-flow compressor or turbine rotors

Country Status (1)

Country Link
GB (1) GB703489A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1284689B (en) * 1962-05-10 1968-12-05 Licentia Gmbh Faceplate stack, e.g. B. composed of face plates and axially clamped runners of a thermal axial turbine, in particular gas turbine
EP1970530A1 (en) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor of a thermal fluid flow engine and fluid flow engine
CN104389644A (en) * 2014-11-15 2015-03-04 哈尔滨广瀚燃气轮机有限公司 Sealing structure for novel turbine motor torsion bearing rotor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1284689B (en) * 1962-05-10 1968-12-05 Licentia Gmbh Faceplate stack, e.g. B. composed of face plates and axially clamped runners of a thermal axial turbine, in particular gas turbine
EP1970530A1 (en) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor of a thermal fluid flow engine and fluid flow engine
WO2008110429A1 (en) * 2007-03-12 2008-09-18 Siemens Aktiengesellschaft Rotor of a gas turbine
CN101631932B (en) * 2007-03-12 2013-01-16 西门子公司 Rotor of a gas turbine
US8641365B2 (en) 2007-03-12 2014-02-04 Siemens Aktiengesellschaft Rotor of a gas turbine
CN104389644A (en) * 2014-11-15 2015-03-04 哈尔滨广瀚燃气轮机有限公司 Sealing structure for novel turbine motor torsion bearing rotor

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