GB810459A - Improved turbomachine rotor with air-cooled blading - Google Patents

Improved turbomachine rotor with air-cooled blading

Info

Publication number
GB810459A
GB810459A GB1713755A GB1713755A GB810459A GB 810459 A GB810459 A GB 810459A GB 1713755 A GB1713755 A GB 1713755A GB 1713755 A GB1713755 A GB 1713755A GB 810459 A GB810459 A GB 810459A
Authority
GB
United Kingdom
Prior art keywords
blade
base
sections
partitions
chambers
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
GB1713755A
Inventor
Bert Eugene Sells
Francis Daniel Doherty
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.)
General Electric Co
Original Assignee
General Electric 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 US347426A priority Critical patent/US2848193A/en
Application filed by General Electric Co filed Critical General Electric Co
Priority to GB1713755A priority patent/GB810459A/en
Publication of GB810459A publication Critical patent/GB810459A/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
    • F01D5/187—Convection cooling
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Landscapes

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

Abstract

810,459. Turbine blades. GENERAL ELECTRIC CO. June 14, 1955, No. 17137/55. Class 110 (3). In a cooled turbine rotor comprising a number of blades fastened to a rotor disc each blade has a base with a blade root portion having a hollow projection thereon to which is attached a separate fabricated upper blade member having front and rear sections and a chamber or chambers formed between them by a partition or partitions secured to one only of the sections or alternately to the sections, the partition or partitions extending radially outwardly and angularly relative to the plane of rotation of the disc when viewed in a plane containing the axis of rotation, the base having a passageway or passageways for conveying cooling fluid to the chambers. The turbine rotor disc 11 which carries a plurality of blades 12 has a flanged member 13 bolted to its side to form a cooling channel 13a which is connected by passages 11c in the rotor to a channel 11b formed by the co-operation of recess 11a in the disc and recess 15b in the base 15 of the blading. The base 15 has a partial blade root portion 16, Fig. 4, shaped to the basic contour of the complete blade and a recessed hollow end portion 16a defined by a fillet 16b. The body 20 of the blade comprises front and back blade sections 21, 22 and dividing partitions 23a, 23b joined respectively thereto defining localized cooling chambers 24, 25, 26. The body 20 can be formed from a single piece of tapered sheet stock welded at one edge 22a or may be formed from two formed or forged pieces welded together along the leading and trailing edges. The body 20 is welded to the base 15 at the fillet 16b. The bottoms of the partitions 23a, 23b are welded or brazed into the slits 17. The partitions 23a, 23b are not radial so that centrifugal force acting on them causes them to press on the front and rear blade sections and thus dampen out blade vibration or parting of the blade member. The chambers 24, 25, 26 are supplied with coolant from the channel 11b through passages 15c.
GB1713755A 1953-04-08 1955-06-14 Improved turbomachine rotor with air-cooled blading Expired GB810459A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US347426A US2848193A (en) 1953-04-08 1953-04-08 Air cooled turbomachine blading
GB1713755A GB810459A (en) 1955-06-14 1955-06-14 Improved turbomachine rotor with air-cooled blading

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1713755A GB810459A (en) 1955-06-14 1955-06-14 Improved turbomachine rotor with air-cooled blading

Publications (1)

Publication Number Publication Date
GB810459A true GB810459A (en) 1959-03-18

Family

ID=10089939

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1713755A Expired GB810459A (en) 1953-04-08 1955-06-14 Improved turbomachine rotor with air-cooled blading

Country Status (1)

Country Link
GB (1) GB810459A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0926311A1 (en) * 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor for a turbomachine
EP1396609A3 (en) * 2002-09-04 2005-05-04 Hitachi, Ltd. Gas turbine with a spacer member and a turbine rotor disk defining an air cooling passage
GB2468722A (en) * 2009-03-21 2010-09-22 Warren Barratt Leigh Carbon fibre wishbone comprising stress uniform fillet
US8708657B2 (en) 2010-01-22 2014-04-29 Rolls-Royce Plc Rotor Disc
CN105156155A (en) * 2015-07-06 2015-12-16 西安交通大学 Vibration reducing and pressure bearing damping structure for blade root platform of movable blades

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0926311A1 (en) * 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor for a turbomachine
EP1396609A3 (en) * 2002-09-04 2005-05-04 Hitachi, Ltd. Gas turbine with a spacer member and a turbine rotor disk defining an air cooling passage
GB2468722A (en) * 2009-03-21 2010-09-22 Warren Barratt Leigh Carbon fibre wishbone comprising stress uniform fillet
US8708657B2 (en) 2010-01-22 2014-04-29 Rolls-Royce Plc Rotor Disc
CN105156155A (en) * 2015-07-06 2015-12-16 西安交通大学 Vibration reducing and pressure bearing damping structure for blade root platform of movable blades

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