US3107897A - Gas turbine nozzle and vane assembly - Google Patents

Gas turbine nozzle and vane assembly Download PDF

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US3107897A
US3107897A US133640A US13364061A US3107897A US 3107897 A US3107897 A US 3107897A US 133640 A US133640 A US 133640A US 13364061 A US13364061 A US 13364061A US 3107897 A US3107897 A US 3107897A
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band
segments
vanes
shroud
annular
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US133640A
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Louis E Varadi
Theodore E Bourque
Daniel M Judge
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General Electric Co
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General Electric Co
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Priority to US133640A priority Critical patent/US3107897A/en
Priority to CH935162A priority patent/CH408959A/en
Priority to FR906522A priority patent/FR1331030A/en
Priority to GB32242/62A priority patent/GB967940A/en
Priority to DEG35770A priority patent/DE1246322B/en
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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

  • gas turine engines typically include a number of nozzle and vane assemblies, such as turbine diaphragm and compressor stator vane assemblies, for directing the air and gas flow within the engine through the rotating compressor and turbine stages.
  • nozzle and vane assemblies such as turbine diaphragm and compressor stator vane assemblies
  • stator vane assemblies for directing the air and gas flow within the engine through the rotating compressor and turbine stages.
  • such assemblies are generally made up of a series of circumferentially spaced stator vanes or nozzle partitions extending radially between inner and outer shrouds which define an annular flow path through the engine.
  • both the inner and outer bands are provided with a series of profiled slots shaped to conform to the contour of the nozzle partitions and through which the nozzle partitions are inserted at assembly and then brazed or otherwise secured in place.
  • the portions of the slots not occupied by the nozzle partitions when the assembly is put together must be filled in with a suitable filler material once the assembly has been completed and the desired alignment relationship obtained. Because the amount of filler material which must be used in some cases becomes quite substantial, this approach has a tendency to adversely affect the structural rigidity and integrity of the assembly which would otherwise be available if the parent metals of the nozzle partitions and the band could be diectly joined along the entire peripheries of the slots.
  • the outer shroud band segments may be moved circumferentially relative to each other into correct alignment.
  • One advantage of this approach is that the overlapped portions, when joined together, provide stifiening ribs in the outer band which contributeto the overall structural integrity of the assembly.
  • the segmented outer band permits the profiled slots in the segments to be formed so as, to very closely conform to the con-tour of the nozzle partitions, thereby greatly reducing the amount of filler material required and permitting the joint strength to approach that of the parent metals.
  • FIG. 1 is a fragmentary view of an annular diaphragm having use in an axial flow compressor or turbine assembly and embodying our invention
  • FIG. 2 is a fragmentary view of the segmented outer band of the annular diaphragm
  • FIG. 3 is a sectional view of the outer band of FIG. 2 along the line 3-3 of FIG. 2 showing one form of circumferentially joining the outer ban-d segments with varying degrees of segment overlap therebetween.
  • annular diaphragm 1 is shown in fragmentary view having use in an axial flow compressor or turbine assembly not shown.
  • the annular diaphragm 1 has an inner shroud 2 having a plurality of radiallyextendin-g stator vanes such as those shown at iii-14.
  • the statorvanes Ill-14 are circumferentially positioned on the outer surface of the inner shroud 2.
  • the stator vanes 10-14 have positioned thereon at a point adjacent the stator vane ends shown at 20-24 an outer shroud 3i which has an inner concentric band'35 and an outerconcentric band 36.
  • the outer band 3-6 is formed by circumferentially joining a plurality of circumjacent outer band segments such as shown at 40-44 to each other to form an integral outer band structure 36.
  • the inner band 35 is formed to a suitable configuration so as to form a generally rectangular cross section in association withthe outer band 36.
  • the outer band 36 is formed of outer band segments 4-il-44which develop overlap areas such as those shown at 50-54 when circumferentially joined to each other to form the integral outer band 36.
  • the individual outer band segments 40-42 have apertures 60-62 positioned through selective segments 40-42.
  • the apertures 60-62 may be formed by any of several machining operations; for example, a punch operation or a cutting operation;
  • the respective apertures 60-62 in the selected outer band seg ments 40-42 receive the stator vane ends Zti-22therethrough in a closely joining relationship since the apertures 69-62 have walls formed to critically conform to the contour of the vane ends 20-22 respectively received therein.
  • the individual outer band segments 40-42 are circumferentially joined to each other b a brazing operation after they have been aligned circumferentially to correctly position the radially extending stator vanes 10- 3 14. The alignment may provide varying segment overlap 79-72 as more clearly shown by FIG. 3.
  • FIG. 3 A cross-sectional view of the outer band 36 along the line 33 of FIG. 2 is shown by FIG. 3 Where the segment overlaps 70-71 of the adjacent outer band segments 40-42 varies with the necessary alignment required prior to the brazing operation.
  • the circumferentially positioned outer band segments 40-44 circurnjacent to the inner band 35 may be joined by butt Welding or by a secondary means such as rivets or bolts inserted through the adjacent outer band segments.
  • FIG. 2 Another desirable advantage of the present invention is shown by FIG. 2 where the segment overlap 70-72 provides stiiiening ribs 80-82 along a non-axial or serpentine line which generally follows the curvature of the vane ends 20-22 in cross section.
  • Such stiffening ribs 80-82 provide a substantially more rigid outer band 36.
  • the respective outer band segments 40-44 may have one or more apertures positioned therethrough to selectively receive the stator vane ends 20-24.
  • the stiffening ribs 80-82 neednot be along a serpentine line as shown since it is considered within the scope of the present invention to provide such stiffening ribs with any suitable contour as may be desired and believed necessary by one having skill in the art.
  • An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
  • An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
  • said inner band having a plurality of apertures therein, (d) a plurality of vanes radially extending from said inner shroud, each of said vanes extending through a respective one of said apertures in said inner band, (e) a plurality of segments circumjacent said inner band comprising said outer band, selected ones of said segments having at least one aperture therein,
  • An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
  • An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
  • an outer shroud comprising a first annular band and a second annular band concentric with and radially spaced from said first band
  • a corresponding circumferential portion of said second hand having a plurality of segments, selected ones of said segments each having an aperture therethrough shaped to conform to the contour of said vanes for receiving a corresponding one of said vanes, said segments thereby being circumferentially positioned relative to each other by said vanes and,

Description

L. E. VARADI ET'AL GAS TURBINE NOZZLE VANE ASSEMBLY Filed Aug. 24, 1961 United States Patent ()fi ice 3,107,897 Patented Oct. 22, 15963 Our invention relates to gas turbine engines and in particular to nozzle and vane assemblies, such as turbine diaphragm and compressor stator vane assemblies, for i i such engines.
As is well known to those skilled in the art, gas turine engines typically include a number of nozzle and vane assemblies, such as turbine diaphragm and compressor stator vane assemblies, for directing the air and gas flow within the engine through the rotating compressor and turbine stages. In the axial flow type of engine, such assemblies are generally made up of a series of circumferentially spaced stator vanes or nozzle partitions extending radially between inner and outer shrouds which define an annular flow path through the engine.
In the case of the turbine diaphragm, it has been a relatively common practice in the design of such structures to form the outer shroud from two or more concentric bands such that in cross section the shroud has a rectangular box-like shape. In such designs both the inner and outer bands are provided with a series of profiled slots shaped to conform to the contour of the nozzle partitions and through which the nozzle partitions are inserted at assembly and then brazed or otherwise secured in place.
Now it will be appreciated that given a construction along the foregoing lines in which two concentric bands are provided with profiled slots which must be aligned at assembly to receive the radially extending nozzle partitions, the slots must either be contoured and positioned with a high degree of accuracy if the necessary alignment relationship is to be provided to receive and properly po sition the nozzle partitions, or if looser tolerances are allowed, then one set of slots must be made substantially oversize in order to allow the necessary relative freedom of movement for alignment purposes at assembly. The requirement for very close tolerances greatly increases the manufacturing expense involved and that approach is generally therefore not used. On the other hand, where the slots are made oversize, the portions of the slots not occupied by the nozzle partitions when the assembly is put together must be filled in with a suitable filler material once the assembly has been completed and the desired alignment relationship obtained. Because the amount of filler material which must be used in some cases becomes quite substantial, this approach has a tendency to adversely affect the structural rigidity and integrity of the assembly which would otherwise be available if the parent metals of the nozzle partitions and the band could be diectly joined along the entire peripheries of the slots.
In view of the foregoing, it is accordingly one object of our invention to provide a new and improved nozzle and vane assembly for gas turbine engines which will facilitate low cost manufacture and at the same time provide a higherdegree of structural rigidity than has hitherto been available.
It is another object of our invention to provide an improved nozzle and vane assembly for gas turbine engines which will permit maintaining critical alignment tolerances between the vanes and nozzles while at the same time permitting the use of low cost and relatively simple manufacturing techniques.
We accomplish these and other objects of our invention in one embodiment thereof as applied to a turbine diaphragm construction, in which the outer shroud is formed Upon assembly of the diaphragm, the outer shroud band segments may be moved circumferentially relative to each other into correct alignment. For reasons which will later be explained in greater detail, we prefer to provide for a circumferential overlap between the adjacent segments of the outer shroud band. One advantage of this approach is that the overlapped portions, when joined together, provide stifiening ribs in the outer band which contributeto the overall structural integrity of the assembly. The segmented outer band permits the profiled slots in the segments to be formed so as, to very closely conform to the con-tour of the nozzle partitions, thereby greatly reducing the amount of filler material required and permitting the joint strength to approach that of the parent metals.
While the specification concludes with claims particularly pointing out and distinctly claiming the subject matter which may be regarded as the invention, the organization and method of operation, together with further objects and advantages thereof, may best be understood by reference to the following description taken in connection with the accompanying drawings in which:
FIG. 1 is a fragmentary view of an annular diaphragm having use in an axial flow compressor or turbine assembly and embodying our invention;
FIG. 2 is a fragmentary view of the segmented outer band of the annular diaphragm;
FIG. 3 is a sectional view of the outer band of FIG. 2 along the line 3-3 of FIG. 2 showing one form of circumferentially joining the outer ban-d segments with varying degrees of segment overlap therebetween.
Referring to the drawing, and particularly to FIG. 1, an annular diaphragm 1 is shown in fragmentary view having use in an axial flow compressor or turbine assembly not shown. The annular diaphragm 1 has an inner shroud 2 having a plurality of radiallyextendin-g stator vanes such as those shown at iii-14. The statorvanes Ill-14 are circumferentially positioned on the outer surface of the inner shroud 2. The stator vanes 10-14 have positioned thereon at a point adjacent the stator vane ends shown at 20-24 an outer shroud 3i which has an inner concentric band'35 and an outerconcentric band 36. In
' accordance with theinvention, the outer band 3-6 is formed by circumferentially joining a plurality of circumjacent outer band segments such as shown at 40-44 to each other to form an integral outer band structure 36. The inner band 35 is formed to a suitable configuration so as to form a generally rectangular cross section in association withthe outer band 36. It will be noted that the outer band 36 is formed of outer band segments 4-il-44which develop overlap areas such as those shown at 50-54 when circumferentially joined to each other to form the integral outer band 36.
As shown by FIG. 2, the individual outer band segments 40-42 have apertures 60-62 positioned through selective segments 40-42. The apertures 60-62 may be formed by any of several machining operations; for example, a punch operation or a cutting operation; The respective apertures 60-62 in the selected outer band seg ments 40-42 receive the stator vane ends Zti-22therethrough in a closely joining relationship since the apertures 69-62 have walls formed to critically conform to the contour of the vane ends 20-22 respectively received therein. The individual outer band segments 40-42 are circumferentially joined to each other b a brazing operation after they have been aligned circumferentially to correctly position the radially extending stator vanes 10- 3 14. The alignment may provide varying segment overlap 79-72 as more clearly shown by FIG. 3.
A cross-sectional view of the outer band 36 along the line 33 of FIG. 2 is shown by FIG. 3 Where the segment overlaps 70-71 of the adjacent outer band segments 40-42 varies with the necessary alignment required prior to the brazing operation. In place of the segment overlap 70-71, the circumferentially positioned outer band segments 40-44 circurnjacent to the inner band 35 may be joined by butt Welding or by a secondary means such as rivets or bolts inserted through the adjacent outer band segments.
Another desirable advantage of the present invention is shown by FIG. 2 where the segment overlap 70-72 provides stiiiening ribs 80-82 along a non-axial or serpentine line which generally follows the curvature of the vane ends 20-22 in cross section. Such stiffening ribs 80-82 provide a substantially more rigid outer band 36.
In accordance with the present invention, other forms of circumierentially segmenting the outer band 36 will be apparent to one skilled in the art. For example, the respective outer band segments 40-44 may have one or more apertures positioned therethrough to selectively receive the stator vane ends 20-24. Thus, it is not critical that a single outer band segment have a single aperture therethrough. Further, certain outer band segments may possibly be formed without apertures to provide spacer elements between related outer band segments which do have apertures therein. Similarly, the stiffening ribs 80-82 neednot be along a serpentine line as shown since it is considered within the scope of the present invention to provide such stiffening ribs with any suitable contour as may be desired and believed necessary by one having skill in the art.
It 'will be observed from the foregoing that we have provided an improved diaphragm construction for axial flow turbines and compressors in which the outer shroud is to be formed of two or more concentric bands. Our construction allows the slots or apertures in the outer band to be formed to conform closely to the contour of the vanes or partitions, thereby providing for superior bonding of the vanes to the band segments, while at the same time allowing low cost manufacturing methods to be used without sacrificing alignment accuracy. In addition, our invention in its preferred form provides additional stifiening ribs on the outer band which even further enhance the structural integrity of the system.
As will be evidenced from the foregoing description, certain aspects of the invention are notlimited to the particular details of construction illustrated, and it is contemplated that other modifications and applications will occur to those skilled in the art. It is, therefore, intended that the appended claims shall cover such modifications and applications that do not depart from the true spirit and scope of the invention.
Having described the invention, what is claimed is:
1. An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
(a) an inner shroud,
(b) an outer shroud having an inner annular band and an outer annular band,
'(c) a plurality of vanes radially extending from said inner shroud through said inner band,
(d) a plurality of segments circumjacent said inner band comprising said outer band,
' (e) selected ones of said segments having at least one aperture therein,
(1) respective ones of said vanes being received in respective ones of said apertures, said segments thereby being circumferentially positioned relative to each other by said vanes,
(g) portions of eachof said relatively positioned segments overlapping the adjacent segments,
(h) and means to circumferentially joint the overlapping portions of said relatively positioned segments (d) a plurality of segments circumjacent said inner band comprising said outer band, (e) selected ones of said segments having at least one aperture therein, (f) respective ones of said vanes being received in respective ones of said apertures, said segments thereby being circumferentially positioned relative to each other by said vanes,
(g) portions of each of said relatively positioned ments overlapping the adjacent segments,
(h) and means to circumferentially join the overlapping portions of said relatively positioned segments to each other along a serpentine line to integrally form the outer annular band.
3. An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
(a) an inner shroud,
(b) an outer shroud having an inner annular band and an outer annular band,
(0) said inner band having a plurality of apertures therein, (d) a plurality of vanes radially extending from said inner shroud, each of said vanes extending through a respective one of said apertures in said inner band, (e) a plurality of segments circumjacent said inner band comprising said outer band, selected ones of said segments having at least one aperture therein,
(g) respective ones of said vanes respective ones of said apertures in said segments, said segments thereby being circumferentially positioned relative to each other by said vanes,
(h) portions of said relatively positioned segments overlapping the adjacent segments,
(1) and means to circumferentially join the overlapping portions of said relatively positioned segments to each other to integrally form the outer annular band. 1
4. An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
(a) an inner shroud, r
(b) an outer shroud having an inner annular band and an outer annular band,
(c) said inner band having a plurality of apertures therein,
(d) a plurality of vanes radially extendingfrom said inner shroud, each of said vanes extending through a respective one of said apertures in said inner band,
(e) a plurality of segments circumjacent said inner, band comprising said outer band, 7
(1") selected ones of said segments having at least one aperture therein,
(g) respective ones of said vanes being/received in respective ones of said apertures in said segments, said segments thereby being circumferentially positionedv relative to each other by said vanes, I I (1:) portions of said relatively positioned segments overlapping the adjacent segments, (i) and means to circumferentially join the overlapping portions of said relatively positioned segments to each other along a serpentineline to integrally form the outer'annular band. 5. An annular diaphragm for use in an axial flow compressor or turbine assembly comprising in combination:
(a) an inner shroud,
being received in (b) an outer shroud comprising a first annular band and a second annular band concentric with and radially spaced from said first band,
(a) a plurality of vanes radially extending from said inner shroud through said outer shroud,
(d) a circumferential portion of said first band comprising a single arcuate member and having a plurality of apertures therethrough for receiving said vanes,
(e) a corresponding circumferential portion of said second hand having a plurality of segments, selected ones of said segments each having an aperture therethrough shaped to conform to the contour of said vanes for receiving a corresponding one of said vanes, said segments thereby being circumferentially positioned relative to each other by said vanes and,
(7) means to circumferentially join the relatively positioned segments to each other to integrally form said second band.
6. An annular diaphragm as defined in claim 5 wherein said segments are joined along a serpentine line.
References Cited in the file of this patent UNITED STATES PATENTS Barth Dec. 31, Koskinen Mar. 24, Jandasek Mar. 24, Stalker Aug. 3, Hunter Apr. 10, Stalker May 13, Lunde et a1. July 14, Stalker May 3, Warnken May 24, Hockert July 19, Welsh Dec. 6, Movsesian Apr. 18, Creek Aug. 15,
FOREIGN PATENTS Great Britain

Claims (1)

1. AN ANNULAR DIAPHRAGM FOR USE IN AN AXIAL FLOW COMPRESSOR OR TURBINE ASSEMBLY COMPRISING IN COMBINATION: (A) AN INNER SHROUD, (B) AN OUTER SHROUD HAVING AN INNER ANNULAR BAND AND AN OUTER ANNULAR BAND, (C) A PLURALITY OF VANES RADIALLY EXTENDING FROM SAID INNER SHROUD THROUGH SAID INNER BAND, (D) A PLURALITY OF SEGMENTS CIRCUMJACENT SAID INNER BAND COMPRISING SAID OUTER BAND, (E) SELECTED ONES OF SAID SEGMENTS HAVING AT LEAST ONE APERTURE THEREIN, (F) RESPECTIVE ONES OF SAID VANES BEING RECEIVED IN RESPECTIVE ONES OF SAID APERTURES, SAID SEGMENTS THEREBY BEING CIRCUMFERENTIALLY POSITIONED RELATIVE TO EACH OTHER BY SAID VANES,
US133640A 1961-08-24 1961-08-24 Gas turbine nozzle and vane assembly Expired - Lifetime US3107897A (en)

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Application Number Priority Date Filing Date Title
US133640A US3107897A (en) 1961-08-24 1961-08-24 Gas turbine nozzle and vane assembly
CH935162A CH408959A (en) 1961-08-24 1962-08-06 Guide vane ring for axial flow machines, in particular gas turbines and compressors
FR906522A FR1331030A (en) 1961-08-24 1962-08-09 Distributor blade assembly
GB32242/62A GB967940A (en) 1961-08-24 1962-08-22 Improvements in turbine or compressor nozzle and vane assembly
DEG35770A DE1246322B (en) 1961-08-24 1962-08-23 Guide vane ring for axial flow machines, especially gas turbines and compressors

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Cited By (11)

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US4243360A (en) * 1978-07-25 1981-01-06 Rolls-Royce Limited Cantilevered structures
US4688992A (en) * 1985-01-25 1987-08-25 General Electric Company Blade platform
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
EP1096108A3 (en) * 1999-11-01 2004-08-11 General Electric Company Stationary flowpath components for gas turbine engines
US20060263213A1 (en) * 2005-05-19 2006-11-23 General Electric Company Steep angle turbine cover buckets having relief grooves
US20080145227A1 (en) * 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies
US20120099961A1 (en) * 2010-10-20 2012-04-26 General Electric Company Rotary machine having non-uniform blade and vane spacing
US20120099996A1 (en) * 2010-10-20 2012-04-26 General Electric Company Rotary machine having grooves for control of fluid dynamics
CN102454425A (en) * 2010-10-20 2012-05-16 通用电气公司 Rotary machine having spacers for control of fluid dynamics
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
US20160177766A1 (en) * 2014-12-18 2016-06-23 United Technologies Corporation Mini blind stator leakage reduction

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GB2445952B (en) * 2007-01-25 2011-07-20 Siemens Ag A gas turbine engine

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US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
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US2945673A (en) * 1951-10-31 1960-07-19 Gen Motors Corp Segmented stator ring assembly
US2963272A (en) * 1957-07-19 1960-12-06 Gen Motors Corp Rotor blade shrouding
US2980396A (en) * 1959-06-29 1961-04-18 Gen Electric Stator construction for turbine engines
US2996281A (en) * 1956-09-05 1961-08-15 Orenda Engines Ltd Mounting ring for blading in a gas turbine engine

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GB190112347A (en) * 1901-06-17 1902-06-17 Charles Algernon Parsons Improvements in and relating to Steam Turbine Blades.
US875644A (en) * 1906-04-09 1907-12-31 Allis Chalmers Steam-turbine.
US2685405A (en) * 1948-05-03 1954-08-03 Edward A Stalker Axial flow compressor
US2632396A (en) * 1949-01-25 1953-03-24 Chrysler Corp Rotor wheel
US2632397A (en) * 1949-02-10 1953-03-24 Chrysler Corp Rotor wheel
US2741455A (en) * 1950-06-29 1956-04-10 Rolls Royce Gas-turbine engines and nozzle-guidevane assemblies therefor
US2945673A (en) * 1951-10-31 1960-07-19 Gen Motors Corp Segmented stator ring assembly
US2937805A (en) * 1952-12-15 1960-05-24 Studebaker Packard Corp Stator blade assembly and method and machine for making same
US2834573A (en) * 1953-06-23 1958-05-13 Stalker Dev Company Rotor construction for fluid machines
US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
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Cited By (17)

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Publication number Priority date Publication date Assignee Title
US4243360A (en) * 1978-07-25 1981-01-06 Rolls-Royce Limited Cantilevered structures
US4688992A (en) * 1985-01-25 1987-08-25 General Electric Company Blade platform
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
EP1096108A3 (en) * 1999-11-01 2004-08-11 General Electric Company Stationary flowpath components for gas turbine engines
US20060263213A1 (en) * 2005-05-19 2006-11-23 General Electric Company Steep angle turbine cover buckets having relief grooves
US7270518B2 (en) * 2005-05-19 2007-09-18 General Electric Company Steep angle turbine cover buckets having relief grooves
US20080145227A1 (en) * 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies
US20120099996A1 (en) * 2010-10-20 2012-04-26 General Electric Company Rotary machine having grooves for control of fluid dynamics
US20120099961A1 (en) * 2010-10-20 2012-04-26 General Electric Company Rotary machine having non-uniform blade and vane spacing
CN102454425A (en) * 2010-10-20 2012-05-16 通用电气公司 Rotary machine having spacers for control of fluid dynamics
US8678752B2 (en) * 2010-10-20 2014-03-25 General Electric Company Rotary machine having non-uniform blade and vane spacing
US8684685B2 (en) * 2010-10-20 2014-04-01 General Electric Company Rotary machine having grooves for control of fluid dynamics
CN102454425B (en) * 2010-10-20 2016-08-03 通用电气公司 There is the rotating machinery of sept for controlling hydrodynamic
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
US20160177766A1 (en) * 2014-12-18 2016-06-23 United Technologies Corporation Mini blind stator leakage reduction
US10018066B2 (en) * 2014-12-18 2018-07-10 United Technologies Corporation Mini blind stator leakage reduction

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GB967940A (en) 1964-08-26
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