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US3269702A - Nozzle vane assembly - Google Patents

Nozzle vane assembly Download PDF

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Publication number
US3269702A
US3269702A US337407A US33740764A US3269702A US 3269702 A US3269702 A US 3269702A US 337407 A US337407 A US 337407A US 33740764 A US33740764 A US 33740764A US 3269702 A US3269702 A US 3269702A
Authority
US
United States
Prior art keywords
ring
vane
shroud
rings
vanes
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 - Lifetime
Application number
US337407A
Other languages
English (en)
Inventor
Arnold D Nichols
Emil E Werstler
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.)
RTX 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
Priority to US337407A priority Critical patent/US3269702A/en
Priority to GB52505/64A priority patent/GB1055069A/en
Priority to NL6415199A priority patent/NL125370C/xx
Priority to DE19651426870 priority patent/DE1426870B2/de
Priority to CH33965A priority patent/CH445524A/de
Priority to SE339/65A priority patent/SE305569B/xx
Priority to FR1715A priority patent/FR1420317A/fr
Priority to BE658208D priority patent/BE658208A/xx
Application granted granted Critical
Publication of US3269702A publication Critical patent/US3269702A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • This invention relates to a vane assembly for a turbine.
  • One feature of the invention is an improved vane attachment and supporting structure. Another feature is an arrangement for securely attaching each vane in position t obtain the benefit of a welded structure but to retain the advantage of individual vane removal if necessary for replacement. Another feature is an arrangement for removal of individual vanes but with each of the vanes held securely in place when assembled and during operation.
  • One feature of the invention is a construction of vanes and supporting structure such that the vanes serve as load-carrying members and provide a bearing supporting structure for the turbine rotor.
  • FIG. 1 is a sectional view through the turbine assembly.
  • FIG. 2 is a sectional View on the line 2-2 of FIG. l.
  • the invention is shown in connection with a free turbine arrangement in which the turbine is supplied by hot gas under pressure from a conventional gas turbine powerplant, the free turbine being located in the exhaust system of the powerplant and receiving and being powered by the exhaust gas from the powerplant.
  • the turbine shown has an annular inlet 2 made up of an outer turbine case 4 and an inner duct wall 6.
  • the turbine case 4 may carry a heat shield 8 which, in effect, forms the outer wall of the gas path.
  • the turbine case is connected as by bolts to an outer nozzle ring 12.
  • the vanes 14 are individual vanes and are attached as by bolts 16 to the outer nozzle ring 12 and by bolts 18 to an inner nozzle ring 20.
  • the latter carries an integral conical bearing support 22, the inner end of which carries a sleeve 24 to support a bearing 26 for the turbine rotor 28.
  • the rotor includes a hub 30 attached to a rotor disc 32 on the periphery of which a row of turbine blades 34 is mounted.
  • the conical structure 22 has bolted to it another conical structure 36 which extends forwardly of the device and carries at its forward end the inner duct wall 6. Suitable 'heat shields 38 may also be carried by the conical structure 22 to shield the bearing 26 and also to form a chamber 40 in which lubricant from the bearing may collect.
  • the turbine vanes 14 are individually attached to the inner nozzle ring by the bolts 18 which extend in a radial direction through circumferential flanges 42 and 44 on each of the inner shrouds 45 integral with the vanes and through cooperating portions of the nozzle ring.
  • the latter has spaced cylindrical surfaces 46 and 46 with which the flanges 42 and 44 are held securely in engagement when the bolts 18 are tightened.
  • the outer shroud element 47 for each vane 14 is bolted securely to the outer nozzle ring 12 by the bolts 16, which, as shown, also extend in a radial direction and hold circumferentially extending flanges 48 and 50 on the shroud element against cylindrical surfaces 52 and 54, respectively, formed on the ring 12.
  • a shoul- Patented August 30, 1966 ICC der 56 at the end ofthe surface 54 may serve tolocate the individual vanes axially of the ring during assembly.
  • the dimensions of the vanes and the inner and outer vane supporting rings are so selected that at steady state condition the vanes and the bolts 16 and 18 are loaded in tension and the load is carried from the outer ring 12 through the vanes and Ithrough the inner ring 20 to hold .the bearing support sleeve 24 securely in concentric relation to the outer vane ring.
  • the relative expansion of the parts may be such that the vanes are stressed in compression rather than tension but the spacing of the flanges 42 and 44 which extendrespectively forwardly and rearwardly of the air flow portion of each of the vanes provides a broad base for support so that in compression the bearing supporting sleeve 24 is still maintained securely in the desired position both radially and axially with respect to the outer ring 12.
  • each of the vanes may be removed individually from the structure by undoing the bolts 16 and 18 which support that particular vane and moving the vane forwardly (to the left in the drawing) and then rotating the inner end of the vane forwardly when the flange 50 comes into contact with the forward portion of the outer ring 12.
  • the case portion 4 and duct 6 will have been removed in order to provide access to the vanes and the supporting bolts so that removal of the vane will be possible.
  • the above described turbine is regularly supported from a supporting structure, not shown, by supports 58 located in a rearward extension 60 on the vane supporting ring 12. In this way the ring 12 remains in position when the outer case member 4 is removed. It will be understood that the inner duct wall 6 is also moved forwardly axially in order to provide for removal of an individual vane but this is easily accomplished by removal of the bolts 62 that hold this duct wall to the conical support 36.
  • a vane attachment including spaced concentric inner and outer supporting rings, the inner ring having axially spaced outer cylindrical surfaces and the outer ring having axially spaced inner cylindrical surfaces, a plurality of circumferentially spaced vanes extending radially between and attached to said rings, each vane having individual inner and outer shroud elements integral therewith, one for each vane, the inner shroud on each vane having axially spaced locating surfaces to engage with the outer cylindrical surfaces on the inner supporting ring, bolts extending substantially radially through said inner ring and said inner shroud for holding said shroud securely and removably against said inner ring and means for attaching the outer shroud elements releasably to the outer ring whereby each vane may be individually removed axially from the rings.
  • a vane attachment for the positioning and removal of individual vanes from the supporting structures, said attachment including inner and outer supporting rings, the inner ring being concentric to the outer ring and having at least two axially spaced outer cylindrical surfaces, and the outer ring having at least two axially spaced inner cylindrical surfaces, a plurality of circumferentially space-d vanes extending radially between said rings, each vane having individual inner and outer shroud elements at opposite ends thereof, one lfor each vane, and each shroud having axially spaced locating surfaces to engage with the surfaces on the adjacent supporting ring, and radially extending bolts extending through said rings and the adjacent shroud elements for holding said vanes securely against the rings in a radial direction.
  • a vane attachment including inner and outer supporting rings, a plurality of circumferentially spaced vanes extending radially between said rings, each vane having individual inner and outer shroud elements thereon at opposite ends for attachment of each vane separately to the inner and outer supporting rings, one of said rings having axially spaced cylindrical locating surfaces thereon for engagement with the associated shroud element, said associated shroud element having axially spaced locating surfaces for engagement with the axially spaced locating surfaces on the ring, bolts extending substantially radially through said associated shroud and the ring for holding said shroud securely against said ring in a radial direction and means for supporting the other shroud on each vane in xed axial relation to the other supporting ring whereby each vane may be individually removed axially from the rings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US337407A 1964-01-13 1964-01-13 Nozzle vane assembly Expired - Lifetime US3269702A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US337407A US3269702A (en) 1964-01-13 1964-01-13 Nozzle vane assembly
GB52505/64A GB1055069A (en) 1964-01-13 1964-12-24 Turbine nozzle vane assembly
NL6415199A NL125370C (ja) 1964-01-13 1964-12-29
DE19651426870 DE1426870B2 (de) 1964-01-13 1965-01-07 Leitschaufelbefestigung fuer eine gasturbine
CH33965A CH445524A (de) 1964-01-13 1965-01-11 Turbinen-Leitschaufel-Befestigung
SE339/65A SE305569B (ja) 1964-01-13 1965-01-12
FR1715A FR1420317A (fr) 1964-01-13 1965-01-13 Dispositif de fixation d'aubes pour turbine
BE658208D BE658208A (ja) 1964-01-13 1965-01-13

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US337407A US3269702A (en) 1964-01-13 1964-01-13 Nozzle vane assembly

Publications (1)

Publication Number Publication Date
US3269702A true US3269702A (en) 1966-08-30

Family

ID=23320435

Family Applications (1)

Application Number Title Priority Date Filing Date
US337407A Expired - Lifetime US3269702A (en) 1964-01-13 1964-01-13 Nozzle vane assembly

Country Status (8)

Country Link
US (1) US3269702A (ja)
BE (1) BE658208A (ja)
CH (1) CH445524A (ja)
DE (1) DE1426870B2 (ja)
FR (1) FR1420317A (ja)
GB (1) GB1055069A (ja)
NL (1) NL125370C (ja)
SE (1) SE305569B (ja)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5222360A (en) * 1991-10-30 1993-06-29 General Electric Company Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
WO1998013585A1 (en) * 1996-09-27 1998-04-02 Chromalloy Gas Turbine Corporation Replacement vane assembly for fan exit guide
US20170167502A1 (en) * 2015-12-14 2017-06-15 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US20170335720A1 (en) * 2016-05-23 2017-11-23 United Technologies Corporation Retention hardware

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2685383B1 (fr) * 1991-12-18 1994-02-11 Snecma Bras structural du carter d'une turbomachine.

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658719A (en) * 1949-10-26 1953-11-10 So Called Cie Electro Mecaniqu Mounting and fixing of turbomachine fixed blades
US2833463A (en) * 1953-11-06 1958-05-06 Rolls Royce Stator construction for axial flow compressor
FR1227668A (fr) * 1958-06-16 1960-08-22 Gen Motors Corp Compresseur à écoulement axial
CA626485A (en) * 1961-08-29 General Motors Corporation Sheet metal compressor casing
US2999670A (en) * 1955-10-18 1961-09-12 Rolls Royce Stator construction for rotary fluid machine
US3026087A (en) * 1957-08-13 1962-03-20 Gen Motors Corp Stator ring assembly
US3042367A (en) * 1958-07-17 1962-07-03 Gen Motors Corp Fluid seal

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA626485A (en) * 1961-08-29 General Motors Corporation Sheet metal compressor casing
US2658719A (en) * 1949-10-26 1953-11-10 So Called Cie Electro Mecaniqu Mounting and fixing of turbomachine fixed blades
US2833463A (en) * 1953-11-06 1958-05-06 Rolls Royce Stator construction for axial flow compressor
US2999670A (en) * 1955-10-18 1961-09-12 Rolls Royce Stator construction for rotary fluid machine
US3026087A (en) * 1957-08-13 1962-03-20 Gen Motors Corp Stator ring assembly
FR1227668A (fr) * 1958-06-16 1960-08-22 Gen Motors Corp Compresseur à écoulement axial
US3042367A (en) * 1958-07-17 1962-07-03 Gen Motors Corp Fluid seal

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5222360A (en) * 1991-10-30 1993-06-29 General Electric Company Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
WO1998013585A1 (en) * 1996-09-27 1998-04-02 Chromalloy Gas Turbine Corporation Replacement vane assembly for fan exit guide
US5765993A (en) * 1996-09-27 1998-06-16 Chromalloy Gas Turbine Corporation Replacement vane assembly for fan exit guide
US20170167502A1 (en) * 2015-12-14 2017-06-15 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US10047763B2 (en) * 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US20170335720A1 (en) * 2016-05-23 2017-11-23 United Technologies Corporation Retention hardware
US10563542B2 (en) * 2016-05-23 2020-02-18 United Technologies Corporation Retention hardware
US11215083B2 (en) 2016-05-23 2022-01-04 Raytheon Technologies Corporation Retention hardware

Also Published As

Publication number Publication date
GB1055069A (en) 1967-01-11
DE1426870B2 (de) 1971-12-30
FR1420317A (fr) 1965-12-03
NL6415199A (ja) 1965-07-14
CH445524A (de) 1967-10-31
NL125370C (ja) 1968-11-15
SE305569B (ja) 1968-10-28
DE1426870A1 (de) 1968-11-21
BE658208A (ja) 1965-04-30

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