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US2945290A - Stator vane half ring assemblies - Google Patents

Stator vane half ring assemblies Download PDF

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Publication number
US2945290A
US2945290A US684136A US68413657A US2945290A US 2945290 A US2945290 A US 2945290A US 684136 A US684136 A US 684136A US 68413657 A US68413657 A US 68413657A US 2945290 A US2945290 A US 2945290A
Authority
US
United States
Prior art keywords
ring
casing
rabbet
cut
circular
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
US684136A
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English (en)
Inventor
Walsh Edward Joseph
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US684136A priority Critical patent/US2945290A/en
Priority to GB27784/58A priority patent/GB868848A/en
Priority to DEG25319A priority patent/DE1121269B/de
Priority to FR1210266D priority patent/FR1210266A/fr
Application granted granted Critical
Publication of US2945290A publication Critical patent/US2945290A/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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to a method of making segmental, stator vane ring assemblies for use in compressors and turbines or the like, particularly compressors and turbines used in gas turbine engines.
  • stator vane assembly in vvhich the stator vanes of each stage are carried by a flexible stator vane ring made up of two halves.
  • the casing is also made up of two halves and each half of the ring is supported in its half of the casing by means of a semi-annular ring rabbet having a semi-annularsupported surface adapted to be supported by a semi-annular supporting surface of a semi-annular casing rabbet.
  • the two semi annular halves of the casing rabbet form an annular rabbet having an annular ring supporting surface and the two halves of each ring rabbet supported by such casing rabbet form an annular ring rabbet having an annular supported surface resting against and supported by the annular supporting surface of such casing rabbet.
  • the supported surfaces of the ring rabbets of the flexible half rings are forced against, and conform to the shape of, the annular supportingsurface of the casing rabbet, the two half rings thereby being forced into an annular shape with the edges thereof abutting against each other.
  • An object of the present invention is to provide an improved inexpensive method for manufacturing segmental stator vane ring assemblies of the type described above, which method simplifies and reduces the cost of manufacture and lends itself to mass production techniques.
  • such method comprises forming a full 360 circular or annular stator vane ring which is relatively flexible as compared to the relatively stiff stator vane casing and easing rabbet.
  • the stator vanes are attached to the full ring and it is cut in at least two places and into at least two segments.
  • the circumference of the annular supported surface of the ring rabbet of the full ring before it is cut into segments is larger than the circumference of the annular supporting surface of the casing rabbet preferably by an amount substantially equal to the sum of the circumferential thicknesses of the cuts.
  • the relatively flexible segments are subsequently inserted in the casing and the supported surfaces thereof are forced into engagement with, and to conform to the contour of, the annular supporting surface of the relatively rigid casing rabbet to thereby force the segments into an annular or circular shape corresponding to the shape of the casing rabbet and cut edges into abutting. relationship'with each other, the diameter and circumference of the resulting annular or circular supported surface of the ring rabbet is substantially the same as the diameter and circumference of the supporting surface of the casing rabbet.
  • the diameter of the circular or '2 annular supported surface of the ring rabbet of the full ring before it is cut into segments is larger than the diameter of the circular or annular supporting surface of the casing rabbet by an amount substantially equal to the gum of the circumferential thicknesses of the cuts divided
  • the ring is cut into halves it is cut at two places and consequently the circumference of the supported surface of the ring rabbet of the full ring is greater than the circumference of the supporting surface of the casing h rabbet by twice the circumferential thickness of each cut.
  • the material removed by the cutting is compensated for and it is possible to subsequently form from the flexible segments a circular ring in which the cut edge of the segments abut against each other and the circular supported surface of the ring rabbet fits snugly against the circular supporting surface of the casing throughout the circumferential'length thereof.
  • Fig. 1 is a partial section in elevation through a compressor stator vane assembly having segmental stator vane ring assemblies made in accordance with the method of the present invention.
  • Fig. 2 is a section taken along the line 2-2 of Fig. l
  • Fig. 3 is aside view ofthe full, oversized stator vane ring prior. to cutting it into segments, the locations at which it is to be out being shown in dotted lines.
  • Fig. 4 is a view in perspective of a partial section taken along the line 4-4 of Fig. 2.
  • Fig. 5 is a view inperspective of a section taken along the line 5-5 of Fig. 3.
  • Fig. 6 is a view similar to Fig. 3 showing the ring after it has been cut.
  • Fig. 7' is a view taken along the line 7-7'of Fig. 1 showing the position of an upper stator vane half ring after it has been inserted in its half of the casing but before it has been forced into its proper semi-circular shape around the casing rabbet.
  • Fig. 8 is a view similar to Fig. 7 showing the position of the upper half ring and its corresponding lower half ring inthe casing'during operation of the turbine when they are forced into proper circular shape around the casing rabbet.
  • 1 comprises a stator vane casing made up of an upper half 2 and a lower half 3 connected together by bolts (not shown) passing through the abutting flanges 4.
  • Each of the halves of the casing is made up of a relatively thin semi-cylindrical casing wall 6 having a pluand extending, at ,rightangles' from the stem 10 in oppo- 3 1 1 site axial directions.
  • Each tongue has a radially outwardly facing supporting surface 14 and forms with stem and casing shell 6 a recess 16 so that each rabbet has a pair of recesses 16 on oppositesides thereof.
  • '.Sur.- face 18 of the web of rabbet18 faces radially inwardly and forms part of the gas passage through 't'he'unit'.
  • a plurality of stages or rows of stator .vanes 20 are mounted on a plurality of flexible ,half .rings 22 made up of a thin flexible and resilient steel as compared to the rigid material and construction of the casing and casing rabbets.
  • the casing rabbet recess is radially wider than the thickness of portion 28 (Fig. 1). w I
  • the supported surfaces 30 of the half rings are held against the supporting surfaces 14 of the casing rabbets thereby forcing the flexible half rings to conform to the circular shape ofthe supportingzsurfaces of the more rigid casing rabbets with the edges 34 of the upper and lower half rings abutting against each other as shown in Fig. 8 in the same plane that the edges 19 of the casing halves abut against each other.
  • the half rings form full rings and the semi-annular ring rabbets form annular ring rabbets which have circular supported surfaces 30 of diameters substantially equal to the diameters of the supporting surfaces 14 against which they are snugly held.
  • Keys (not shown) are associated with the edges 19 and 34 to lock the ring halves from rotating in the casing.
  • the present invention provides a novel inexpensive method of making the half ring assemblies.
  • a 360 full ring 36 (Fig. 3) is formed out of flexible, resilient material and a plurality of vanes 20 are mounted on it.
  • the diameter of the circular supported surface 30 of this full ring is indicated as b in Fig. 3.
  • the full 360 ring 36 is cut at 38 into halves 22, the thickness of each cut being indicated as c and being exaggerated in Figs. 3 and 6.
  • Fig. 6 shows the two half ringsZZ which are obtained.
  • the circumferential thickness of the material removed by each cut is the same as the thickness of the out.
  • each ring rabbet of the full ring 36 before it is' cut and hence before any material is removed therefrom by the cuts is larger than the circumference of the circular supporting surface 14 of the casing rabbet 8 of the assembled casing halves by an amount equal to the sum of the circumferential thicknesses c of the cuts. Consequently, when each half of the cut ring is placed in the casing half and the semi-annular surfaces 30 thereof are forced into engagement with, and to conform to the contour of, the supporting surfaces "14,afterthe halves of the casing are assembled, the cut edges 34 are forced into abutting relationship with each other as shown "in Fig. 8 and the surfaces 30 of the .two half rings form circular surfaces having substantially the same circumference and diameter as the surface 14.
  • K is the circumference of the surface 30' of 'thefull'ring
  • K the circumference of the surface 14, n ,is thenumber'of cuts and c is the circumferential thickness of each cut
  • K is substantially equal to K -l-nc.
  • the diameter of the surface 30 of the full ring 36 is larger than the diameter of the surface 14 by an amount equal to the sum of the circumferential thicknesses of the cuts divided by 1:", or b is substantially equal to Furthermore, in the full ring 36 the circumferential distance d (Fig. 3) between the two vanes 20 between which each saw-cut is to be made is greater than the circumferential distance e between the other vanes by an amount which is equal to the circumferential thickness of the saw cut so that after the ring has been cut and the two halves are inserted in the casing halves and are forced to conform to the circular shape of the supporting.
  • each half of the cut ring is inserted into place in its casing half by inserting one'end of the half ring into one end of the space 32 with the rabbets 24 of the ring being inserted into the oppositely facing recesses 16 of adjacent rabbets 8, whereafter the flexible and resilient half ring is slid circumferentially around the recesses and space into'the position shown in Fig. 7.
  • the flexibility of the half ring permits it to be bent sufliciently to be so inserted and the resiliency thereof causes the ends of the ring to spring outwardly as shown in Fig. 7. After all the half rings are in place the two halves of the casing are bolted together.
  • a Means are provided (not shown) so that at least during operation the surfaces 30 of the half rings are yieldably forced into engagement with the supporting surfaces 14 of the casing rabbets so as to closely conform thereto whereupon the cut edges 34 of the two half rings are forced into abutting relationship with each other as shown in Fig. 8 to form a complete circular ring, the circular ring rabbet surfaces 30 of which have a diameter substantially equal to the diameter a of the circular casing rabbets 8.
  • One convenient way of doing this is by means 7 of air or other gas under pressure in the spaces 32.
  • the preferred embodiment of the present invention reif a rigid, oversized 360 ring is used the cut halves thereof will not subsequently take on the contour of the casing rabbet supporting surfaces.
  • the cut segments can be forced into a circular shape conforming to the contour of the casing rabbet supporting surface although the full ring originally has a different diameter.
  • the method of the present invention provides an inexpensive and easy way to make segmental, stator vane ring assemblies as compared to methods in which each segment must be made, and hence machined, separately.
  • the ring is separated into halves and hence requires two cuts 38, it may be separated into any number of segments. However, the greater the number of segments, the greater the number of cuts required. Consequently, the sum of the circumferential thicknesses of such cuts is increased and the diameter of the full ring 36 must be increased accordingly.
  • circular and annular as referred to herein with respect to supporting surface 14 and supported surface 30 include embodiments in which the tongues 12 and the rabbet portions 28 are notched so that such surfaces are not continuous.
  • the circumference of circular surface 30 in the assembled unit is equal to the circumference of the surface 14 when the two surfaces are in intimate contact with each other along their circumferential lengths, which is the most desirable arrangement. In practice, however, it is sometimes difiicult to achieve this intimate contact so that these circumferences are not always exactly equal. However, so long as they are substantially equal the construction is satisfactory. The same applies to the circularity of the various parts.
  • a method of making a segmental stator vane ring adapted to be supported in a stator vane casing by a substantially circular supporting surface of a substantially circular casing rabbet associated with said casing comprising forming a substantially circular, flexible ring having a substantially circular ring rabbet with a substantially circular supported surface, cutting said circular ring in at least two places and into at least two segments, the diameter of said supported surface before said ring is cut into segments being larger than the diameter of said supporting surface by an amount equal to substantially the sum of the circumferential thicknesses of said cuts divided by 1r, inserting said flexible segments in said casing and forcing the supported surfaces thereof into engagement with, and to conform to the contour of, said supporting surface of said casing rabbet.
  • a method of making a segmental stator vane ring adapted to be supported in a stator vane casing by a substantially circular supporting surface of a substantially circular casing rabbet associated with said casing comprising forming a substantially circular, flexible ring having a substantially circular ring rabbet with a substantially circular supported surface, cutting said ring in at least two places and into at least two segments, the circular supported surface of said ring before it is cut having a circumference greater than the circumference of said supporting surface of said casing rabbet by an amount equal to the sum of the circumferential thicknesses of said cuts, inserting said flexible segments in said casing, and forcing the supported surfaces thereof into engagement with, and to conform to the contour of, said supporting surface of said casing rabbet.
  • a method according to claim 2 wherein a plurality of vanes are assembled on said ring before it is cut into segments, the distance between the adjacent vanes which are to be separated by each cut being greater than the distance between the other vanes by an amount equal to the circumferential thickness of the cut, whereby in the assembled segmental ring, said vanes are spaced from each other a distance equal to the distance between said other vanes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US684136A 1957-09-16 1957-09-16 Stator vane half ring assemblies Expired - Lifetime US2945290A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US684136A US2945290A (en) 1957-09-16 1957-09-16 Stator vane half ring assemblies
GB27784/58A GB868848A (en) 1957-09-16 1958-08-29 Segmental stator vane ring for a compressor or turbine
DEG25319A DE1121269B (de) 1957-09-16 1958-09-16 Verfahren zur Herstellung aus Segmenten bestehender Tragringe einer Leitschaufelanordnung fuer Axialverdichter
FR1210266D FR1210266A (fr) 1957-09-16 1958-09-16 Procédé de fabrication des demi-anneaux d'ailettes de stator, destinés aux compresseurs et aux turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US684136A US2945290A (en) 1957-09-16 1957-09-16 Stator vane half ring assemblies

Publications (1)

Publication Number Publication Date
US2945290A true US2945290A (en) 1960-07-19

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Family Applications (1)

Application Number Title Priority Date Filing Date
US684136A Expired - Lifetime US2945290A (en) 1957-09-16 1957-09-16 Stator vane half ring assemblies

Country Status (4)

Country Link
US (1) US2945290A (de)
DE (1) DE1121269B (de)
FR (1) FR1210266A (de)
GB (1) GB868848A (de)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
US3797085A (en) * 1972-08-22 1974-03-19 Air Canada Method of repairing a part having eroded or damaged guide vanes
US3869775A (en) * 1971-09-28 1975-03-11 Albert C Smith Liquid propulsion apparatus and method of fabrication
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
US4014627A (en) * 1974-08-21 1977-03-29 Shur-Lok International S.A. Compressor stator having a housing in one piece
US4489468A (en) * 1982-06-24 1984-12-25 Elliott Turbomachinery Co., Inc. Method of providing a multivalve turbine nozzle ring interface seal
USRE32685E (en) * 1981-04-01 1988-05-31 General Electric Company Double flow reheat diaphragm
EP0331837A1 (de) * 1988-01-11 1989-09-13 General Electric Company Leitschaufelbefestigung für Turbinen
US4953282A (en) * 1988-01-11 1990-09-04 General Electric Company Stator vane mounting method and assembly
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
US5232340A (en) * 1992-09-28 1993-08-03 General Electric Company Gas turbine engine stator assembly
US20030082051A1 (en) * 2001-10-31 2003-05-01 Snecma Moteurs Fixed guide vane assembly separated into sectors for a turbomachine compressor
US20050100438A1 (en) * 2003-11-10 2005-05-12 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US7278821B1 (en) * 2004-11-04 2007-10-09 General Electric Company Methods and apparatus for assembling gas turbine engines
US20090136348A1 (en) * 2007-11-27 2009-05-28 Philippe Bonniere Vibration damping of a static part using a retaining ring
FR2976314A1 (fr) * 2011-06-07 2012-12-14 Snecma Aube en materiau composite pour stator
US20140056702A1 (en) * 2012-08-22 2014-02-27 United Technologies Corporation Mounting lug for connecting a vane to a turbine engine case
US20150308278A1 (en) * 2014-04-24 2015-10-29 Techspace Aero S.A. Integral Bent Housing for an Axial Turbomachine Compressor
US20190055850A1 (en) * 2017-08-17 2019-02-21 United Technologies Corporation Tuned airfoil assembly

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117843B (en) * 1982-04-01 1985-11-06 Rolls Royce Compressor shrouds
DE3341871A1 (de) * 1983-11-19 1985-05-30 Brown, Boveri & Cie Ag, 6800 Mannheim Axialverdichter

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1402849A (en) * 1921-06-18 1922-01-10 Gen Aluminum & Brass Mfg Co Method of making bearings or the like
US2230637A (en) * 1937-12-15 1941-02-04 Admos Bleibronze Dr Springorum Method of making bearing bushings
US2543355A (en) * 1947-02-17 1951-02-27 Rolls Royce Stator for axial compressors
US2610786A (en) * 1946-06-25 1952-09-16 Gen Electric Axial flow compressor
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
US2848156A (en) * 1956-12-18 1958-08-19 Gen Electric Fixed stator vane assemblies

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1402849A (en) * 1921-06-18 1922-01-10 Gen Aluminum & Brass Mfg Co Method of making bearings or the like
US2230637A (en) * 1937-12-15 1941-02-04 Admos Bleibronze Dr Springorum Method of making bearing bushings
US2610786A (en) * 1946-06-25 1952-09-16 Gen Electric Axial flow compressor
US2543355A (en) * 1947-02-17 1951-02-27 Rolls Royce Stator for axial compressors
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
US2848156A (en) * 1956-12-18 1958-08-19 Gen Electric Fixed stator vane assemblies

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
US3869775A (en) * 1971-09-28 1975-03-11 Albert C Smith Liquid propulsion apparatus and method of fabrication
US3797085A (en) * 1972-08-22 1974-03-19 Air Canada Method of repairing a part having eroded or damaged guide vanes
US4014627A (en) * 1974-08-21 1977-03-29 Shur-Lok International S.A. Compressor stator having a housing in one piece
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
USRE32685E (en) * 1981-04-01 1988-05-31 General Electric Company Double flow reheat diaphragm
US4489468A (en) * 1982-06-24 1984-12-25 Elliott Turbomachinery Co., Inc. Method of providing a multivalve turbine nozzle ring interface seal
EP0331837A1 (de) * 1988-01-11 1989-09-13 General Electric Company Leitschaufelbefestigung für Turbinen
US4868963A (en) * 1988-01-11 1989-09-26 General Electric Company Stator vane mounting method and assembly
US4953282A (en) * 1988-01-11 1990-09-04 General Electric Company Stator vane mounting method and assembly
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
US5232340A (en) * 1992-09-28 1993-08-03 General Electric Company Gas turbine engine stator assembly
EP1308630A1 (de) * 2001-10-31 2003-05-07 Snecma Moteurs Statorsektor für einen Verdichter eines Turbotriebwerks
FR2831615A1 (fr) * 2001-10-31 2003-05-02 Snecma Moteurs Redresseur fixe sectorise pour compresseur d'une turbomachine
US20030082051A1 (en) * 2001-10-31 2003-05-01 Snecma Moteurs Fixed guide vane assembly separated into sectors for a turbomachine compressor
US6890151B2 (en) 2001-10-31 2005-05-10 Snecma Moteurs Fixed guide vane assembly separated into sectors for a turbomachine compressor
US20050100438A1 (en) * 2003-11-10 2005-05-12 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US7033135B2 (en) * 2003-11-10 2006-04-25 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US7413399B2 (en) 2003-11-10 2008-08-19 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US20090104028A1 (en) * 2003-11-10 2009-04-23 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US7278821B1 (en) * 2004-11-04 2007-10-09 General Electric Company Methods and apparatus for assembling gas turbine engines
US20090136348A1 (en) * 2007-11-27 2009-05-28 Philippe Bonniere Vibration damping of a static part using a retaining ring
US8197189B2 (en) 2007-11-27 2012-06-12 Pratt & Whitney Canada Corp. Vibration damping of a static part using a retaining ring
FR2976314A1 (fr) * 2011-06-07 2012-12-14 Snecma Aube en materiau composite pour stator
US20140056702A1 (en) * 2012-08-22 2014-02-27 United Technologies Corporation Mounting lug for connecting a vane to a turbine engine case
US9546571B2 (en) * 2012-08-22 2017-01-17 United Technologies Corporation Mounting lug for connecting a vane to a turbine engine case
US20150308278A1 (en) * 2014-04-24 2015-10-29 Techspace Aero S.A. Integral Bent Housing for an Axial Turbomachine Compressor
US10196909B2 (en) * 2014-04-24 2019-02-05 Safran Aero Boosters Sa Method for producing an integral bent housing for an axial turbomachine compressor
EP2937516B1 (de) * 2014-04-24 2020-04-01 Safran Aero Boosters SA Rundgebogenes Monoblock-Gehäuse für Kompressor einer axialen Turbomaschine und entsprechendes Fertigungsverfahren
US20190055850A1 (en) * 2017-08-17 2019-02-21 United Technologies Corporation Tuned airfoil assembly
US10876417B2 (en) * 2017-08-17 2020-12-29 Raytheon Technologies Corporation Tuned airfoil assembly

Also Published As

Publication number Publication date
FR1210266A (fr) 1960-03-08
GB868848A (en) 1961-05-25
DE1121269B (de) 1962-01-04

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