US2984454A - Stator units - Google Patents

Stator units Download PDF

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Publication number
US2984454A
US2984454A US679623A US67962357A US2984454A US 2984454 A US2984454 A US 2984454A US 679623 A US679623 A US 679623A US 67962357 A US67962357 A US 67962357A US 2984454 A US2984454 A US 2984454A
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US
United States
Prior art keywords
vane
vanes
support
axially
flange
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
US679623A
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English (en)
Inventor
Bruno M Fiori
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
Priority to NL230456D priority Critical patent/NL230456A/xx
Priority to NL99435D priority patent/NL99435C/xx
Priority to BE570533D priority patent/BE570533A/xx
Priority to US679623A priority patent/US2984454A/en
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to DEU5516A priority patent/DE1114364B/de
Priority to FR1211581D priority patent/FR1211581A/fr
Priority to GB26924/58A priority patent/GB893579A/en
Priority to CH362269D priority patent/CH362269A/de
Application granted granted Critical
Publication of US2984454A publication Critical patent/US2984454A/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

  • ⁇ It is still a further object of this invention to permit turbine rotor bladeinspectionr and removal by baring the rotor blades thru removal of the vanes ofthe adjacent stator unit.
  • Fig. 1 is a cross-sectional showing of my stator unit.
  • ⁇ Fi ⁇ g ⁇ .,2 is a viewtaken along line 2,-2 of Fig. ⁇ 1.
  • Figs. 3 and 4 show alternate connecting and locking means which maybe used to fasten the vane inner end tothe vane inner support.
  • Patent No. 2,770,946 atmospheric air is introduced into ⁇ the compressor of a modern aircraft turbojet yengine and passed in compressed form into the combustion chamber for heating.
  • the heated and compressed air is their ⁇ passed thru the turbine which performs a power extrae#1 tion function to drive the compressor and possibly a propeller, and after passing thru the turbine Vthe engine gases are discharged to atmosphere thru an exhaust out;A4
  • Both the axial flow compressor and the axial ow tur? bine consist basically Aof alternate rows of stationary vanes and moveable vanes, sometimes called blades.
  • the stationary vanes are supported in position as part of a ⁇ stator unit while the moveable blades rotate with a re- ⁇ volving disc.
  • the stator unit andthe vanes thereon perform the function of turning the Powerplant gas such that itis directed against the rotating blades immediately .'downstream thereof at the proper angle.
  • axial flow turbine 10 having an axis or centerline ⁇ and rotor unit'12 which comprises a plurality of radially extendi ing blades 14 attached torand equally spaced circumferentially about the periphery of disc 16 for rotation u therewith.
  • Stator unit 18 ⁇ comprises a plurality of stationary vanes 20 which are ⁇ individually supported at their inner end by vane inner support 22 and at their outer end by vane outer support 24.
  • Vane outer support 24 comprises axially directed ring l2.6 Iwhich forms acircle about turbine and powerplant axis or centerline (not- A shown) and which is supported by and may be integral Ring 26 carriesv with one-piece outer turbine case l28.
  • Ring 126 includes a ⁇ plurality ofradiallydirectedlholes 36 lwhich are spaced' equally circumfer” entially' thereabout to receive, in positive fashionr'suclias" apnCh-t, or interlocking threads, radially directed outer vane support fpins or lugs 38.
  • Ring26 ⁇ further comprises?v radiallydirected rflange 40 against which anti-erosion andfthrust strip 42 bears.
  • Connecting means 44 attaches strip 42 to ring 2'6 and may be in the form of a ⁇ rivet.
  • Flange 62 has a plurality-.of axially directed apertures 7i) passingA therethruy'to receivein positive fashion, such as a pinch-t or interi locking thread, axially extending inner vane support pin' or lug 72.
  • a plurality lof stationaryvanes 20 areradiallydirectedl'f and equally ,spaced ⁇ circumferentiallybet-Ween vane"V innerf support 22 and ⁇ vane outer support 24 and each vanec20- ⁇ is positively positioned in stator unit 18, both ⁇ at -its inner, ⁇ end 74 and at its outer end 76, independently of all other; ⁇ vanes 20. ⁇ lt will be noted that inner endr74. of vallei. ⁇
  • stator unit illustratingl 3 2.0 .tamarins 'twg axially. flanges or lugs 78 and 80 which are joined by member 82 and which are fabricated such that the inner surface 84 ofitheaxiallynforward flange ⁇ 7 8, is of greater height and of'lesser radial ldistance from theiturbine axis than is,-
  • ⁇ in axially forwardsupport vilange 62 passes thru aperture 90 of vane flange 78 and extends axially forward thereof and carries the necessary hole therethru to permit locking the parts in this position by the use of lock wire 92 such that the lock wire passes thru the two adjacent pins or rivets 72, as best shown in Fig. 2.V
  • Figs. 3 and 4 show alternate vane inner end attaching and locking means.
  • Fig. 3 shows bolt 94 passing thru vane flange 84 and support flange 62', into which it is lixedly threaded.
  • Aperture 96 is provided to permit locking bolt 94 in position by lock wire (not shown).
  • Fig, 4 shows bolt.98 projecting thru vane flange 84" and support flange 6'2 and threadedlyengaging insert 100 which is attached in any convenient fashion to support flange 62".
  • Aperture 102 is provided to permit the locking of bolt 98 in position by means ofV lock wirer (not shown).y
  • Aperture 102 is provided to permit the locking of bolt 98 in position by means ofV lock wirer (not shown).y
  • vane inner. end 74 is axially positioned by support flanges 62 and 64 and is crcumferentially and radially fixed by rivet, lug or pin 72.
  • vAt the outer end 76 of vane 20 is received loosely by pin or lug 38 to axially Aand circumferentially position outer end 76 of vane 20 and a substantial radial distance exists .between vane platform 54 and ring 26 of vane outer support 24, thereby permitting relative radial movement therebetween.
  • Lug 38 preferably passes thru platform 54 in a location to be substantially equidistant between the side walls of vane L20.
  • transition duct 104 is located immediately upstream or axially forward of stator unit 18 and engages outer vane support 24 in sealing relation by seal 106 and engages inner vane flange 78 in sealing relation by seal'i108.
  • Surface 109 of seal 108 is positioned to provide axial support to the vane inner end thru flange 78 in case of back pressure or backfire. Reverse axial loading goes from ange 78 to seal 108, to transition duct i104 and to support member 126.
  • Transition duct 104 and combustion chamber support 110 may be removed by disengaging connecting means 112 and 114 after the combustion chamber (not shown) has been removed.
  • This bares lock wire 92 for removal which will permit the removal of bolts 94 and 98 in Figs. 3 and 4, respectively, to free the inner ends 74 of vane 20 in the conligurations shown in Figs. 1, 3 and 4, thereby permitting same to be moved radially inward, if desired, and then pivoted axially forward about pin 38 or merely pivoted axially forward about pin 38 due to the loose lit existing between 'pin 38 and platform 54, thereby releasing the outer end 76 of vane 20 to free the vane for removal from stator unit 18.
  • a single vane 20 may be released, removed and replaced thru access from the upstream or axially forward side of stator unit 18 only, without disturbingthe .other vanes in any way.
  • vane inner support 22 isy attached to structural members 126 of turbine 10 byconnecting means 124.
  • the engine case or combustion chamber case may then be placed in position to envelop the series of,
  • a stator unit of circular cross-section for use in a powerplant having an axis comprising a plurality of vanes, each having a hole in one end thereof, means for supporting each of said vanes in its operative position to be substantially radially extending and substantially van equal radial distance from and equally spaced in a circle.l about said axis, means providing access to one side of.'
  • said vanes and support means including a Aplurality of substantially radially extending pins each received loosely in one of said holes in said vanes and a plurality of readily releasable means each accessible from .said one side and each fully supporting the other end of one of said vanes thereby permitting the removal and replacement of any vane in said plurality from said oneside while maintaining all other vanes in Y operative position.
  • a .stator unit of circular cross-section for use in a powerplant having an axis comprising a plurality of vanes, each having a hole in the outer end thereof, means to4 support said vanes to be substantially radially extending and substantially an equal radial distance from and equally spaced in a circle aboutY said axis including first means supporting the outer end of each of said .vanes individually and independently of all other vanes and second means independent of said first means supporting the inner end of each of said vanes individually and inden pendently of all other vanes Vsaid rst means including a ring enveloping said vanes and having a plurality of substantially radially inwardly directed pins each received loosely in one of said holes in said vanesV and said second,
  • means including a plurality of readily releasable means porting each of said vanes in its operative position to be substantially radially extending and substantially an equal radial distance from and equally spaced in a circle about said axis, and means providing access to said side of said vanes and support means.
  • a stator unit comprising a vane outer support cornprising a ring, a vane inner support comprising at least one radially extending circular flange, a plurality of vanes each having an axially extending platform at its outer end and at least one radially extending ilange at its inner end and with said vanes extending radially between and spaced circumferentially about said vane supports and each located with respect thereto such that said radially extending flanges are juxtapositioned and further such that said vane outer support ring and each of said vane platforms is spaced a preselected distance apart radially, a plurality of radially directed lugs each connected to said vane outer support ring and projecting loosely thru one of said vane platforms to position the vane outer end, a plurality of axially directed lugs each connected to said vane inner support flange and projecting thru the inner end flange of one of said vanes and projecting therebeyond to position said vane inner end,
  • a stator unit having an axis and comprising a vane outer support comprising a ring, a vane inner support comprising two axially spaced rings forming radially extending circular ilanges of different inner diameters such that the axially forward flange is of lesser diameter, a plurality of vanes each having an axially extending platform at its outer end and two axially spaced radially extending flanges at its inner end and with the axially forward vane flange of greater height and with said vanes extending radially between and spaced circumferentially about said vane supports and each located with respect thereto such that said radially extending flanges are juxtapositioned with said axially forward vane iange engaging the axially forward support flange on the axially forward side thereof and with the other flanges engaging in the same relative axial positions and further such that said vane outer support ring and each of said vane platforms is spaced a preselected distance apart radially, a pluralit
  • a stator unit having an axis and comprising a vane outer support comprising an axially extending ring forming a circle about said axis, an anti-erosion and thrust ring attached to said vane outer support ring, cooling gas passages in said outer support ring positioned to direct Cooling sas carer Said-,antil-emsionand thrustting, axane inner support olprisins .two axially spaced.
  • a turbine or compressor unit having an axis and comprising a rotor unit and a stator unit coaxial therewith and positioned axially forward thereof,l said rotor unit comprising a plurality of removable radially extending blades attached to the periphery of a rotatable disc and equally spaced thereabout, said stator runit.
  • a vane outer support comprising an axially extending ring forming a circle about said axis, an anti-erosion and thrust ring attached to said vane outer support ring, cooling gas passages in said outer support ring positioned to direct cooling gas over said anti-erosion and thrust ring
  • a vane inner support comprising two axially spaced rings forming radially extending circular flanges of different inner diameters such that the axially forward flange is of lesser diameter
  • a plurality of vanes ⁇ aligned with said blades each having an axially extending platform at its outer end and two axially spaced radially extending flanges at its inner end and with the axially forward vane flange of greater height and with said vanes extending radially between and spaced circumferentially about said vane supports and each located with respect thereto such that said radially extending flanges are juxtapositioned with said axially forward vane flange engaging the axially yforward
US679623A 1957-08-22 1957-08-22 Stator units Expired - Lifetime US2984454A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
NL230456D NL230456A (sv) 1957-08-22
NL99435D NL99435C (sv) 1957-08-22
BE570533D BE570533A (sv) 1957-08-22
US679623A US2984454A (en) 1957-08-22 1957-08-22 Stator units
DEU5516A DE1114364B (de) 1957-08-22 1958-08-02 Eintrittsleitvorrichtung fuer Gasturbinen
FR1211581D FR1211581A (fr) 1957-08-22 1958-08-21 Stators pour turbines, compresseurs et machines analogues
GB26924/58A GB893579A (en) 1957-08-22 1958-08-21 Improvements relating to stator units for use in rotary power plants utilizing compressors or turbines
CH362269D CH362269A (de) 1957-08-22 1958-08-22 Leitapparat an einer Turbomaschine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US679623A US2984454A (en) 1957-08-22 1957-08-22 Stator units

Publications (1)

Publication Number Publication Date
US2984454A true US2984454A (en) 1961-05-16

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ID=24727658

Family Applications (1)

Application Number Title Priority Date Filing Date
US679623A Expired - Lifetime US2984454A (en) 1957-08-22 1957-08-22 Stator units

Country Status (7)

Country Link
US (1) US2984454A (sv)
BE (1) BE570533A (sv)
CH (1) CH362269A (sv)
DE (1) DE1114364B (sv)
FR (1) FR1211581A (sv)
GB (1) GB893579A (sv)
NL (2) NL230456A (sv)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3062499A (en) * 1960-05-18 1962-11-06 United Aircraft Corp Vane mounting and seal
US3075744A (en) * 1960-08-16 1963-01-29 United Aircraft Corp Turbine nozzle vane mounting means
US3423071A (en) * 1967-07-17 1969-01-21 United Aircraft Corp Turbine vane retention
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
US4512712A (en) * 1983-08-01 1985-04-23 United Technologies Corporation Turbine stator assembly
DE3445835A1 (de) * 1983-12-19 1985-07-11 General Electric Co., Schenectady, N.Y. Blechplatte
US4883407A (en) * 1987-12-16 1989-11-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Screwed attachment of a body of revolution to an annular flange in a turbine engine
WO1996004468A1 (en) * 1994-08-01 1996-02-15 United Technologies Corporation Vibration damping shroud for a turbomachine vane
WO2004029415A1 (en) * 2002-09-26 2004-04-08 Siemens Westinghouse Power Corporation Heat-tolerant vortex-disrupting fluid guide arrangement
US20060123797A1 (en) * 2004-12-10 2006-06-15 Siemens Power Generation, Inc. Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine
US20140366556A1 (en) * 2013-06-12 2014-12-18 United Technologies Corporation Gas turbine engine vane-to-transition duct seal

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1086432A (en) * 1965-09-21 1967-10-11 Bristol Siddeley Engines Ltd Gas turbine engines
US4425078A (en) * 1980-07-18 1984-01-10 United Technologies Corporation Axial flexible radially stiff retaining ring for sealing in a gas turbine engine
US4478551A (en) * 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US4720236A (en) * 1984-12-21 1988-01-19 United Technologies Corporation Coolable stator assembly for a gas turbine engine
DE10133393B4 (de) 2001-07-13 2007-08-30 TransMIT Gesellschaft für Technologietransfer mbH Röhrchen mit Innendurchmessern im Nanometerbereich

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB609682A (en) * 1946-03-20 1948-10-05 Power Jets Res & Dev Ltd Improvements in or relating to turbines
US2488875A (en) * 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
US2494821A (en) * 1946-03-25 1950-01-17 Rolls Royce Means for supporting the nozzles of the combustion chambers of internal-combustion turbines
US2606742A (en) * 1947-04-03 1952-08-12 Napier & Son Ltd Blades of axial flow compressors and turbines and the means of fixing them
GB741794A (en) * 1952-12-22 1955-12-14 Gen Motors Corp Improvements in turbine nozzles
US2833514A (en) * 1953-06-01 1958-05-06 Armstrong Siddeley Motors Ltd Construction of turbine stator blades
US2838275A (en) * 1952-10-03 1958-06-10 Vickers Electrical Co Ltd Gas turbines

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB589542A (en) * 1941-09-22 1947-06-24 Karl Baumann Improvements in internal combustion turbines
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB609682A (en) * 1946-03-20 1948-10-05 Power Jets Res & Dev Ltd Improvements in or relating to turbines
US2651492A (en) * 1946-03-20 1953-09-08 Power Jets Res & Dev Ltd Turbine
US2494821A (en) * 1946-03-25 1950-01-17 Rolls Royce Means for supporting the nozzles of the combustion chambers of internal-combustion turbines
US2606742A (en) * 1947-04-03 1952-08-12 Napier & Son Ltd Blades of axial flow compressors and turbines and the means of fixing them
US2488875A (en) * 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
US2838275A (en) * 1952-10-03 1958-06-10 Vickers Electrical Co Ltd Gas turbines
GB741794A (en) * 1952-12-22 1955-12-14 Gen Motors Corp Improvements in turbine nozzles
US2833514A (en) * 1953-06-01 1958-05-06 Armstrong Siddeley Motors Ltd Construction of turbine stator blades

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3062499A (en) * 1960-05-18 1962-11-06 United Aircraft Corp Vane mounting and seal
US3075744A (en) * 1960-08-16 1963-01-29 United Aircraft Corp Turbine nozzle vane mounting means
US3423071A (en) * 1967-07-17 1969-01-21 United Aircraft Corp Turbine vane retention
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
US4512712A (en) * 1983-08-01 1985-04-23 United Technologies Corporation Turbine stator assembly
DE3445835A1 (de) * 1983-12-19 1985-07-11 General Electric Co., Schenectady, N.Y. Blechplatte
US4883407A (en) * 1987-12-16 1989-11-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Screwed attachment of a body of revolution to an annular flange in a turbine engine
WO1996004468A1 (en) * 1994-08-01 1996-02-15 United Technologies Corporation Vibration damping shroud for a turbomachine vane
WO2004029415A1 (en) * 2002-09-26 2004-04-08 Siemens Westinghouse Power Corporation Heat-tolerant vortex-disrupting fluid guide arrangement
US6884029B2 (en) 2002-09-26 2005-04-26 Siemens Westinghouse Power Corporation Heat-tolerated vortex-disrupting fluid guide component
US20060123797A1 (en) * 2004-12-10 2006-06-15 Siemens Power Generation, Inc. Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine
US7527469B2 (en) * 2004-12-10 2009-05-05 Siemens Energy, Inc. Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine
US20140366556A1 (en) * 2013-06-12 2014-12-18 United Technologies Corporation Gas turbine engine vane-to-transition duct seal
US9963989B2 (en) * 2013-06-12 2018-05-08 United Technologies Corporation Gas turbine engine vane-to-transition duct seal

Also Published As

Publication number Publication date
GB893579A (en) 1962-04-11
NL230456A (sv)
DE1114364B (de) 1961-09-28
FR1211581A (fr) 1960-03-17
BE570533A (sv)
CH362269A (de) 1962-05-31
NL99435C (sv)

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