US2605997A - Mounting for the guide vanes of axial-flow compressors and turbines - Google Patents

Mounting for the guide vanes of axial-flow compressors and turbines Download PDF

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Publication number
US2605997A
US2605997A US727520A US72752047A US2605997A US 2605997 A US2605997 A US 2605997A US 727520 A US727520 A US 727520A US 72752047 A US72752047 A US 72752047A US 2605997 A US2605997 A US 2605997A
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US
United States
Prior art keywords
axial
rings
ring
vanes
supporting structure
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Expired - Lifetime
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US727520A
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English (en)
Inventor
Lombard Adrian Albert
Morley Frederick Willia Walton
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Rolls Royce PLC
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Rolls Royce PLC
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Publication date
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    • 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 guide vanes for axial flow turbines and compressors of the type in which the blades are mounted between inner and outer rings.
  • This invention has for its object to provide means for minimising distortion or displacement of 'the blades in such blade mountings during assembly and inuse.
  • a nozzle guide vane assembly for-axial flow turbines and compressors of the typeset forth in which guide vanes are mounted at their inner and outer ends respectively in inner and outer rings so as to be located circumferentially relative thereto and to have freedom in the eneral axial sense thereof, except at one point in axial section where such freedom is'restra'ined by anchorage of, one of the vane ends to, the associated ring.
  • each guide vane is mounted in the two rings respectively so as to be located relatively to the rings transversely of the length of the said vane-ends but to be free to move relatively to the rings in the general direction of the length of said vane-ends except at one point in one end where that end is also located on the associated ring in said direction.
  • each vane is loosely splined to each ring and is formed with a projecting foot at one corner to engage an open-ended recess in one ring and to be retained therein by another part closing the open end of the recess.
  • Figure 1 is a sectional elevation of a part of a nozzle guide vane assembly.
  • Figure 2 is a section on the line 2-2 of Figure 1, g
  • Figure 3 is a view similar to Figure 1 and showing an alternative and preferred embodiment o'f'the invention.
  • Figure 4 is a section on the line 4-4 of Figure 3. 7
  • the nozzle guide 'vane which is generally indicated by the reference numeral '5, comprises a vane portion 6 integrally formed at each end with a tablet l, 8. Each tablet is a parallelogram or rectangle in form when the vane-is viewed end-on.
  • the vane is mounted between an'i'nner-ring 9' and an outer (and concentric) ring IObysliding the inner and outer tablets l, 8 respectively into slots ll formed '10 Claims. (01. ass-'77) apart of the vane shroud.
  • the slots being helically disposed'of' the, rings and the tablets arranged to. mat-ch therewith.
  • Each tablet isa'lojose, fit in its. slot so that, the ends of vane 5 .are loosely splinedtfio rin s 3 and It.
  • the slots H there are produced splines l2 and it is arrangfidthat theirdepth be that of their associated tablets. .In this way the splines lie flush with the internal surfaces of the tablets 7, 8 (see Figure 2), and constitute The tablet o'f eac'h vane isformedwith a foot l3 projecting from one, side race thereof and the "foot engages-,ina recess M inringfl ( Figure '1).
  • the inner and outer rings 9 and HI respectively are secured to.
  • each tablet- 'i', 8' is formed respectively with a spline IT and i8 on its exterior surface to engage the slots.
  • the foot i3! is formed atone end of the inner spline H.
  • the central part of each spline l-i and; I8, is machined away, as at Hi, to reduce the tendency :forthey vaneto bind in the rings. This construction is preferred because as thegtablets nearly abut-they form the complete shroud and shield the support rings from the-hot gases.
  • the guide vanes :5" can be assembled in rings 9? and [0 without risk of distortion, which is present if they are riveted or welded to the rings, end-each vane is located at one corner only (by foot t3) so that it can expand freely both radially and axially of the rings.
  • the inner and outer rings can move axially and circum-ferentially relative to each other, due, for instance, to temperature themselves and without displacing them, thus possibly varying their passage shape or throat area.
  • the present invention is thus particularly applicable to the nozzle guide vanes for an internal combustion turbine in that the risk of distortion due to-the high temperature at which such vanes operate is minimised.
  • the vanes will be Y subjected only to stresses resulting from gas pressure and are not stressed as the result of differential expansion of the vanes and rings.
  • the minimisation of distortion is of importance as it reduces variations in the throat area between the trailing edge of each vane and the adjacent vane on its concave side, which area controls the work capacity of such turbines.
  • a plurality of guide vane members having tablets formed at the outer and inner ends of the vanes, the tablets atthe outer ends of the vanes each engaging a slot in the outer ring and the tablets at the inner ends of the vanes each engaging a slot in the inner ring and said tablets lying flush within the slots to constitute at least a part of shroud rings for the vanes, and means locating in an axial direction one of the tablets associated with each guide vane at one end only of its slot permitting free expansion and contraction of said vanes relatively to said rings in an axial and a radial direction.
  • a supporting structure an outer ring secured to the supporting structure and having its inner surface slotted a plurality of circumferentially spaced slots
  • an inner ring secured to the supporting structure in the plane of the outer ring and having its outer surface slotted by a plurality of circumferentially spaced slots, the sides of said slots in both rings extending across the rings from one edge thereof in a direction having an axial component
  • a plurality of guide vane members having tablets formed at the outer and inner ends of the vanes, the tablets at the outer ends of the vanes each engaging a slot in the outer ring and the tablets at the inner ends of the vanes each engaging a slot in the inner ring
  • a projecting foot at one end of one of the tablets associated with each guide vane, an open-ended recess in the ring engaged by said tablet receiving the said foot within it, and means closing the end of said recess to locate said end of the tablet in an axial and radial direction.
  • a supporting structure an outer ring secured to the supporting structure and having on its inner surface a plurality of circumferentially spaced slots of which the sides extend across the ring from one edge thereof in a direction having an axial component
  • an inner ring secured to said supporting structure in the plane of the said outer ring and having on its outer surface a plurality of circumferentially spaced slots of which the sides extend across the ring from the edge thereof corresponding to said edge of said outer ring in a direction having an axial component
  • a plurality of guide-vanes each formed with a tablet at each end, said tablets respectively engaging a slot in said outer ring and a slot in said inner ring and lying flush therein to constitute at least a part of shroudrings for said vanes and means locating in an axial direction one tablet of each guide-vane at one end only of its slot.
  • a supporting structure an outer ring secured to the supporting structure and having on its inner surface a plurality of circumferentially spaced slots of which the sides extend across the ring from one edge thereof in a direction having an axial component
  • an inner ring secured to said supporting structure in the plane of the said outer ring and having on its outer surface a plurality of circumferentially spaced slots of which the sides extend across the ring from the edge thereof corresponding to said edge of said outer ring in a direction having an axial component
  • a plurality of guide-vanes each formed with a tablet at each end, a projecting foot at one end of one tablet of each vane, an open-ended recessin the ring engaged by said tablet receiving said foot Within it and means closing th end of said recess to locate the said tablet and vane in an axial and a radial direction.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US727520A 1946-04-05 1947-02-10 Mounting for the guide vanes of axial-flow compressors and turbines Expired - Lifetime US2605997A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB257532X 1946-04-05
GB30147X 1947-01-03

Publications (1)

Publication Number Publication Date
US2605997A true US2605997A (en) 1952-08-05

Family

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Family Applications (1)

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US727520A Expired - Lifetime US2605997A (en) 1946-04-05 1947-02-10 Mounting for the guide vanes of axial-flow compressors and turbines

Country Status (5)

Country Link
US (1) US2605997A (it)
BE (1) BE487115A (it)
CH (1) CH257532A (it)
FR (1) FR944756A (it)
GB (1) GB611326A (it)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2915280A (en) * 1957-04-18 1959-12-01 Gen Electric Nozzle and seal assembly
US2937000A (en) * 1957-08-16 1960-05-17 United Aircraft Corp Stator units
US3072380A (en) * 1959-02-05 1963-01-08 Dresser Ind Stator blade carrier assembly mounting
DE1221849B (de) * 1960-08-16 1966-07-28 United Aircraft Corp Axial-Gasturbine
DE1278178B (de) * 1966-06-10 1968-09-19 Rolls Royce Eintrittsleitschaufelkranz fuer Axialverdichter von Gasturbinentriebwerken
US3423071A (en) * 1967-07-17 1969-01-21 United Aircraft Corp Turbine vane retention
US4861229A (en) * 1987-11-16 1989-08-29 Williams International Corporation Ceramic-matrix composite nozzle assembly for a turbine engine
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US20090155068A1 (en) * 2007-12-13 2009-06-18 Eric Durocher Radial loading element for turbine vane
US20140169957A1 (en) * 2012-12-19 2014-06-19 Honeywell International Inc. Turbine nozzles with slip joints and methods for the production thereof
RU2523938C2 (ru) * 2008-08-26 2014-07-27 Снекма Турбина высокого давления газотурбинного двигателя, кольцеобразный фланец, сектор направляющих лопаток и авиационный двигатель, содержащий турбину высокого давления
US20140255174A1 (en) * 2012-12-21 2014-09-11 United Technologies Corporation Manufacture of full ring strut vane pack
EP2995777A1 (en) * 2014-09-09 2016-03-16 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US20220251962A1 (en) * 2019-07-08 2022-08-11 MTU Aero Engines AG Guide vane having a support portion rib

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2932485A (en) * 1954-10-01 1960-04-12 United Aircraft Corp Stator construction
DE1067971B (it) * 1955-10-18 1959-10-29
GB2192233B (en) * 1986-07-02 1990-11-28 Rolls Royce Plc A gas turbine engine load transfer structure
US5494402A (en) * 1994-05-16 1996-02-27 Solar Turbines Incorporated Low thermal stress ceramic turbine nozzle

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191016889A (en) * 1910-07-15 1910-10-20 James Howden Improvements in Means for Fixing Blades in Turbines.
US2402418A (en) * 1943-01-20 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191016889A (en) * 1910-07-15 1910-10-20 James Howden Improvements in Means for Fixing Blades in Turbines.
US2402418A (en) * 1943-01-20 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2915280A (en) * 1957-04-18 1959-12-01 Gen Electric Nozzle and seal assembly
US2937000A (en) * 1957-08-16 1960-05-17 United Aircraft Corp Stator units
US3072380A (en) * 1959-02-05 1963-01-08 Dresser Ind Stator blade carrier assembly mounting
DE1221849B (de) * 1960-08-16 1966-07-28 United Aircraft Corp Axial-Gasturbine
DE1278178B (de) * 1966-06-10 1968-09-19 Rolls Royce Eintrittsleitschaufelkranz fuer Axialverdichter von Gasturbinentriebwerken
US3423071A (en) * 1967-07-17 1969-01-21 United Aircraft Corp Turbine vane retention
US4861229A (en) * 1987-11-16 1989-08-29 Williams International Corporation Ceramic-matrix composite nozzle assembly for a turbine engine
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US20090155068A1 (en) * 2007-12-13 2009-06-18 Eric Durocher Radial loading element for turbine vane
US8096746B2 (en) * 2007-12-13 2012-01-17 Pratt & Whitney Canada Corp. Radial loading element for turbine vane
RU2523938C2 (ru) * 2008-08-26 2014-07-27 Снекма Турбина высокого давления газотурбинного двигателя, кольцеобразный фланец, сектор направляющих лопаток и авиационный двигатель, содержащий турбину высокого давления
US20140169957A1 (en) * 2012-12-19 2014-06-19 Honeywell International Inc. Turbine nozzles with slip joints and methods for the production thereof
US9702252B2 (en) * 2012-12-19 2017-07-11 Honeywell International Inc. Turbine nozzles with slip joints and methods for the production thereof
US20140255174A1 (en) * 2012-12-21 2014-09-11 United Technologies Corporation Manufacture of full ring strut vane pack
EP2995777A1 (en) * 2014-09-09 2016-03-16 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US11041392B2 (en) 2014-09-09 2021-06-22 Raytheon Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US20220251962A1 (en) * 2019-07-08 2022-08-11 MTU Aero Engines AG Guide vane having a support portion rib

Also Published As

Publication number Publication date
BE487115A (it)
FR944756A (fr) 1949-04-14
CH257532A (de) 1948-10-15
GB611326A (en) 1948-10-28

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