GB981476A - Gas turbine engine vane assembly - Google Patents

Gas turbine engine vane assembly

Info

Publication number
GB981476A
GB981476A GB4352863A GB4352863A GB981476A GB 981476 A GB981476 A GB 981476A GB 4352863 A GB4352863 A GB 4352863A GB 4352863 A GB4352863 A GB 4352863A GB 981476 A GB981476 A GB 981476A
Authority
GB
United Kingdom
Prior art keywords
wall
guide vanes
section
gas turbine
vane
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
GB4352863A
Inventor
Arthur Bill
George Oulianoff
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 GB4352863A priority Critical patent/GB981476A/en
Priority to DE1964R0039158 priority patent/DE1301643B/en
Publication of GB981476A publication Critical patent/GB981476A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0058—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with vertical jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/022—Multi-stage pumps with concentric rows of vanes

Landscapes

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

Abstract

981,476. Gas turbine stator blade mounting; jet propulsion plant; axial flow compressors. ROLLS-ROYCE Ltd. Nov. 4, 1963, No. 43528/63. Headings F1C, F1J and FIT. A gas turbine engine vane assembly comprises two concentric substantially V-section annular parts the open ends of which face towards opposite sides of the assembly and each of which has a wall which is secured to a wall of the other V-section part, the other wall of each V-section part having angularly spaced slots therein through each of which extends the root portion of a vane, and means for securely mounting the root portion of each vane within the respective V-section part. A stator vane mounting assembly for a ducted fan gas turbine jet propulsion engine having two coaxial independent shafts, Fig. 2, comprises an annular support structure 26 carrying fan outlet guide vanes 25 and compressor inlet guide vanes 27 which are respectively also connected to the outer casing 11 and bearing support 30. Structure 26 is connected to the inner casing 12 and comprises two substantially V-section concentric annular members 33, 34, Fig. 4, which point respectively upstream and downstream. Wall 35 of member 33 is connected to wall 36 of member 34 and the members 33, 34 are also connected to axially spaced rings 43, 44. The fan outlet guide vanes 25 are mounted in slots 42 in the wall 41 of member 34 and retained by blocks 50, 51, Fig. 3. Each blade root 47 is stiffened by a sleeve 52 and a lip 53 on the sleeve supports fairing sections 54. The compressor inlet guide vanes 27 are similarly mounted in slots in wall 40 of member 33. The V-section members 33, 34 and guide vanes 25, 27 are formed of resin bonded or fibrous reinforced material and are cemented together. In a modification, the radially outer ends of the guide vanes 25 are also mounted in a V-section member attached to the casing 11.
GB4352863A 1963-11-04 1963-11-04 Gas turbine engine vane assembly Expired GB981476A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB4352863A GB981476A (en) 1963-11-04 1963-11-04 Gas turbine engine vane assembly
DE1964R0039158 DE1301643B (en) 1963-11-04 1964-11-02 Support ring for concentrically nested guide vanes of a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4352863A GB981476A (en) 1963-11-04 1963-11-04 Gas turbine engine vane assembly

Publications (1)

Publication Number Publication Date
GB981476A true GB981476A (en) 1965-01-27

Family

ID=10429146

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4352863A Expired GB981476A (en) 1963-11-04 1963-11-04 Gas turbine engine vane assembly

Country Status (2)

Country Link
DE (1) DE1301643B (en)
GB (1) GB981476A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3351319A (en) * 1966-09-01 1967-11-07 United Aircraft Corp Compressor and fan exit guide vane assembly
US3494539A (en) * 1967-04-03 1970-02-10 Rolls Royce Fluid flow machine
US5161949A (en) * 1990-11-28 1992-11-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.M.C.A." Rotor fitted with spacer blocks between the blades
US20160108748A1 (en) * 2013-06-04 2016-04-21 United Technologies Corporation Gas turbine engine with dove-tailed tobi vane

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3827680A1 (en) * 1988-08-16 1990-02-22 Mtu Muenchen Gmbh Device for fixing a guiding grate, made of titanium, of an axial-flow compressor to a compressor housing made of a fibre-reinforced plastic

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1009349B (en) * 1953-12-31 1957-05-29 Schnakenberg & Co Aug Centrifugal machine runner
GB789733A (en) * 1954-03-22 1958-01-29 Rolls Royce Improvements in or relating to structural elements for axial-flow compressors or turbines or the like machines
US2934317A (en) * 1954-05-05 1960-04-26 Studebaker Packard Corp Prestressed compressor blade
DE1761314U (en) * 1957-12-06 1958-02-13 Orenstein & Koppel Ag CYLINDER HEAD FOR COMPRESSOR.
US2961150A (en) * 1958-12-30 1960-11-22 Gen Electric Frame structure for turbo-machine
GB937826A (en) * 1961-05-02 1963-09-25 Rolls Royce Engine driven fan

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3351319A (en) * 1966-09-01 1967-11-07 United Aircraft Corp Compressor and fan exit guide vane assembly
US3494539A (en) * 1967-04-03 1970-02-10 Rolls Royce Fluid flow machine
US5161949A (en) * 1990-11-28 1992-11-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.M.C.A." Rotor fitted with spacer blocks between the blades
US20160108748A1 (en) * 2013-06-04 2016-04-21 United Technologies Corporation Gas turbine engine with dove-tailed tobi vane
US10494938B2 (en) * 2013-06-04 2019-12-03 United Technologies Corporation Gas turbine engine with dove-tailed TOBI vane
US11092025B2 (en) 2013-06-04 2021-08-17 Raytheon Technologies Corporation Gas turbine engine with dove-tailed TOBI vane

Also Published As

Publication number Publication date
DE1301643B (en) 1969-08-21

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