GB936508A - Improvements relating to vane or blade members for compressors or turbines - Google Patents

Improvements relating to vane or blade members for compressors or turbines

Info

Publication number
GB936508A
GB936508A GB917661A GB917661A GB936508A GB 936508 A GB936508 A GB 936508A GB 917661 A GB917661 A GB 917661A GB 917661 A GB917661 A GB 917661A GB 936508 A GB936508 A GB 936508A
Authority
GB
United Kingdom
Prior art keywords
vane
spring
mandrel
chuck
walls
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
GB917661A
Inventor
Arthur Richards Redsell
Norman Howard Jeffrey
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 GB917661A priority Critical patent/GB936508A/en
Publication of GB936508A publication Critical patent/GB936508A/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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

936,508. Turbine and compressor blades. ROLLS-ROYCE Ltd. March 12, 1962 [March 13, 1961], No. 9176/61. Class 110 (3). An inlet or nozzle guide vane or compressor or turbine stator blade member, has an internal chamber in which resilient means make an interference fit with and exert an outward pressure on the walls of the member. The vane has an outer wall 10, Fig. 3, enclosing a chamber containing support tubes 11, 12, heating or cooling air supply tube 13 and coil springs 15, 16 which make an interference fit with the walls. Prior to insertion in the vane, each spring is twisted to reduce its coil diameter by mounting on a mandrel 18 carried by a chuck 19, gripping one end of the spring and rotating the chuck. The free end of the spring is then clamped, mandrel 18 removed from the chuck 19 and inserted with the spring into the vane. The clamping device is released to allow the spring to untwist and press against the walls of the vane 10. A top cover seals the chamber. Alternatively, the coil diameter of the spring can be reduced by stretching and locking it in the stretched state on the mandrel 18. The spring may be embedded in a moulded silicone rubber strip before stretching on the mandrel, and the external surfaces of the strip coated with silicone grease or adhesive before inserting into the vane and unlocking on the mandrel. Any part of the mandrel projecting out of the vane may be cut off, or the mandrel may be removed and the space in the spring filled with silicone rubber which is foamed by heat treatment to effect vibration damping.
GB917661A 1961-03-13 1961-03-13 Improvements relating to vane or blade members for compressors or turbines Expired GB936508A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB917661A GB936508A (en) 1961-03-13 1961-03-13 Improvements relating to vane or blade members for compressors or turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB917661A GB936508A (en) 1961-03-13 1961-03-13 Improvements relating to vane or blade members for compressors or turbines

Publications (1)

Publication Number Publication Date
GB936508A true GB936508A (en) 1963-09-11

Family

ID=9866875

Family Applications (1)

Application Number Title Priority Date Filing Date
GB917661A Expired GB936508A (en) 1961-03-13 1961-03-13 Improvements relating to vane or blade members for compressors or turbines

Country Status (1)

Country Link
GB (1) GB936508A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4162136A (en) * 1974-04-05 1979-07-24 Rolls-Royce Limited Cooled blade for a gas turbine engine
FR2478196A1 (en) * 1980-03-14 1981-09-18 Rolls Royce DAMPING OF TURBOMACHINE BLADES

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4162136A (en) * 1974-04-05 1979-07-24 Rolls-Royce Limited Cooled blade for a gas turbine engine
FR2478196A1 (en) * 1980-03-14 1981-09-18 Rolls Royce DAMPING OF TURBOMACHINE BLADES

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