US3887976A - Stator blade assembly for turbo machines - Google Patents

Stator blade assembly for turbo machines Download PDF

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Publication number
US3887976A
US3887976A US335973A US33597373A US3887976A US 3887976 A US3887976 A US 3887976A US 335973 A US335973 A US 335973A US 33597373 A US33597373 A US 33597373A US 3887976 A US3887976 A US 3887976A
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Prior art keywords
ring
blades
series
blade
apertures
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US335973A
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J Rodger Sheilds
Alexander A Carroll
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Elliott Turbomachinery Co Inc
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Individual
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Assigned to ELLIOTT TURBOMACHINERY CO., INC. reassignment ELLIOTT TURBOMACHINERY CO., INC. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: CARRIER CORPORATION, A CORP OF DEL.
Assigned to FIRST NATIONAL BANK OF CHICAGO, THE reassignment FIRST NATIONAL BANK OF CHICAGO, THE LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: ELLIOT TURBOMACHINERY CO., INC.
Assigned to CONTINENTAL BANK N.A. reassignment CONTINENTAL BANK N.A. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ELLIOTT TURBOMACHINERY CO., INC.
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P11/00—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for 
    • B23P11/02—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for  by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • 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
    • Y10T29/49826—Assembling or joining
    • Y10T29/49863—Assembling or joining with prestressing of part

Definitions

  • stator blades of a stage of an axial flow turbo machine are assembled in an arcuate series, as by inser- Related Appllcanon Data tion of the journals at the outer ends of the blades in [62 ⁇ Division of Ser. No, 112,163. Feb. 3, 1971, the stator housing.
  • a one-piece arcuate inner shroud abandoned ring is formed with aperture spaced circumferentially comparable to the spacing of the inner ends of the Cl 29/1563 29/446; 415/217; blades in the series.
  • Force is apll'llt. to the ends f the ring to ontrol or bow the Field Or Search 29/1558 446, same sufficiently to permit insertion of the contracted 415/217. 8, 219 ring into the series of blades.
  • the contracting force is relieved, permitting the [56] RefETBIICeS Clled ring to expand to normal contour whereby the inner UNITED STATES PATENTS journals of the blades become positioned in the aper- 839243 12906 Wilkinson IIIIIIIIIIIIIII 219N563 R tures of the ring.
  • annular bearings are in-
  • stator blades are fixedly mounted in the stator housing by locking the tangs. or journals. at the outer ends of the blades to the stator housing.
  • stator blades are subjected to forces of substantial magnitude tending to create a vibratory condition in the blades.
  • inner shroud rings have been fixedly secured to the inner ends of the fixed blades; for example. as shown in US. Pat. No. 3.269.701. assigned to the assignee herein.
  • This invention has as an object a stator blade assembly structure wherein the inner shroud ring is of simple one-piece construction. economical to manufacture and which is quickly and conveniently mounted on the inner ends of an arcuate series of stator blades.
  • stator blades of a stage are arranged in an arcuate series. which arrangement can be had by inserting the journals at the outer ends of the blades in apertures formed in the stator housing. and a one-piece shroud ring of arcuate configuration is formed with oversized apertures to receive projections at the inner ends of the circular series of blades.
  • the ring is applied to the blades of the series by being contracted to reduce the chord dimension of the ring sufficient to clear the inner ends of the blades when the ring is inserted in the series.
  • the ring Upon release of the contraction force. the ring expands to its normal contour. moving the apertures of the ring over the journals at the inner ends of the blades. With the ring so positioned. in the arcuate series of stator blades.
  • annular bearing members are in serted in the apertures and have a close running fit with the ends of the blades. The bearings are locked in the apertures.
  • FIG. 1 is a schematic illustration showing a preferred embodiment of the invention wherein the blades of a stage of the machine are arranged in an arcuate series in the stator housing. and illustrating the inner shroud ring in contracted form positioned for insertion in the series of blades. the housing and shroud ring being illus' trated in sections.
  • FIG. 2 is a view similar to FIG. I showing the shroud ring inserted farther in the series of blades.
  • FIG. 3 is an enlarged view taken on line III-III of FIG. 2.
  • FIG. 4 is an enlarged sectional view of the inner shroud ring and blade journal structure shown in FIG. 3.
  • the shaft structure ofthe turbo machine is designated 10, and has affixed to it a series of axially arranged discs II.
  • Each disc 11 carries a circular series of rotor blades 12, there being a disc and series of blades 12 for each stage of the machine.
  • the blades 12 are encircled by a stator housing 13 which conventionally consists of two semi-circular sections having side bosses l bolted together.
  • a circular series of stator blades 17 is mounted intermediate each series of spaced rotating blades 12.
  • the blades 17 are provided at their outer ends with projections in the form of tangs 20. which extend outwardly through apertures formed in the stator housing 13.
  • stator blades I7 are provided with projections or journals. which may be formed integral with the blades. or as shown in FIG. 4. may consist of annular collar members positioned on a tang portion 27, the outer end of which is headed over as shown at 28 to fixedly secure the collars 25 to the blades I7.
  • the journals 25 are formed with radial flanges 26 abutting against the inner end of the blade.
  • a one-piece shroud ring section 30 shown in the pre ferred embodiment as being of semi-circular form. is provided with a series of apertures 33 spaced circumferentially along the ring comparable to the spacing of the inner ends of the blades I7. These apertures have a bore somewhat larger than the diameter of the collars 25 as indicated by the annular space 35. FIG. 4. encircling the periphery of the collar 25. These apertures are dimensioned so that upon applying a contracting force inwardly on the ends of the ring 30. as by rods 37 and turnbuckle 40. FIGS. I and 2. the ring is deflected to reduce the chordal dimension thereof sufficiently within its elastic limit. to permit the contracted ring to be inserted in the circular series. of blades 17. mounted in the half of the stator housing 13.
  • the aperture in the contracted ring 30, adjacent one end thereof. is placed over the journal of the blade I7 at the corresponding end of the series of blades.
  • the ring is then rocked downwardly whereby the journals of the blades successively enter the apertures ofthe ring.
  • the ring has been rocked downwardly to a position where the journal of the blade at the center of the series is about to enter the corresponding aperture in the ring.
  • the turnbuckle 40 is then released permitting the ring to expand to normal contour. whereby the journals of the remaining blades 17 in the series enter the remaining apertures in the ring.
  • the expanded ring being indicated by dotted outline 41, FIG. 2.
  • Annular bearing members are then inserted in the space between the periphery of each collar 25 and the bore of the aperture 33.
  • the bearings have a snug fit with the bore in the apertures. and a close running fit with the collars 25.
  • the bores of the apertures are formed with circular grooves to receive snap rings SI. FIG. 4.
  • Thrust washers 53 are positioned between the snap ring and the bearings 50. Wlth this arrangement.
  • the bearings are detachably interlocked with the ring 30, and a thrust structure is provided for the journaled stator blades 17.
  • the inner shroud rings 30 are economically produced by a turning operation. and are completed by the drilling and grooving of the apertures 33.
  • the rings may be formed circular and subsequently split to provide the two integral semi-circular sections for use in each stage of the machine. This one-piece formation of the shroud ring greatly reduces the time and effort in the assembly of the shroud rings in the machine.
  • the stator housing 13, illustrated in FIGS. 1 and 2 may be the half section of the housing associated with the bottom half of the machine casing. After the stator blades 17 have been assembled in the stator housing for each stage. and the ring 30 attached to the inner ends of the blades. the rotor assembly is lowered into the machine.
  • shroud ring assembly struc ture of our invention permits the shroud ring to be formed in two semi-circular sections which are manufactured at low cost and are easily and quickly assembled in the machine.
  • the construction serving as the subject matter of this invention provides a more reliable structure'than in previous shroud ring constructions. as for example. the two-piece bolted sections adapted to clamp the inward projecting ends of the stator blades at opposite sides thereof as disclosed in U.S. Pat. No. 3.269.701.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The stator blades of a stage of an axial flow turbo machine are assembled in an arcuate series, as by insertion of the journals at the outer ends of the blades in the stator housing. A onepiece arcuate inner shroud ring is formed with aperture spaced circumferentially comparable to the spacing of the inner ends of the blades in the series. The diameter of the apertures exceeds the diameter of the blade journals. Force is applied to the ends of the ring to control or bow the same sufficiently to permit insertion of the contracted ring into the series of blades. Upon insertion of the ring, the contracting force is relieved, permitting the ring to expand to normal contour whereby the inner journals of the blades become positioned in the apertures of the ring. Thereafter annular bearings are inserted in the space between the journals and the bores of the apertures.

Description

United States Patent Sheilds et al.
1 1 June 10, 1975 [541 Q BLADE ASSEMBLY FOR TURBO FOREIGN PATENTS OR APPLICATIONS MA INES 15.893 7/1908 United Kingdom 415/217 [76] Inventors: J. Rodger Sheilds, 1601 Penn Ave.
Pittsburgh, Pa. 15206; Alexander A. Primary Examiner w Lanham Carroll, 30m Assistant ExaminerDan C. Crane Greensburg, Pa. 15601 [22] Filed: Feb. 26, 1973 [57] ABSTRACT [211 App]. 335,973 The stator blades of a stage of an axial flow turbo machine are assembled in an arcuate series, as by inser- Related Appllcanon Data tion of the journals at the outer ends of the blades in [62} Division of Ser. No, 112,163. Feb. 3, 1971, the stator housing. A one-piece arcuate inner shroud abandoned ring is formed with aperture spaced circumferentially comparable to the spacing of the inner ends of the Cl 29/1563 29/446; 415/217; blades in the series. The diameter of the apertures ex- 4l5/219 R ceeds the diameter of the blade journals. Force is apll'llt. to the ends f the ring to ontrol or bow the Field Or Search 29/1558 446, same sufficiently to permit insertion of the contracted 415/217. 8, 219 ring into the series of blades. Upon insertion of the ring, the contracting force is relieved, permitting the [56] RefETBIICeS Clled ring to expand to normal contour whereby the inner UNITED STATES PATENTS journals of the blades become positioned in the aper- 839243 12906 Wilkinson IIIIIIIIIIIIIIIIII 219N563 R tures of the ring. Thereafter annular bearings are in- |5g 755 [M915 w 4 Y v H 5 g R serted in the space between the journals and the bores 1,621,002 3/1927 Dimberg 29/1568 R of the apertures, 2,856,118 10/1958 Smith r 1. 415/217 3 Cl 4 D 1212.317 2/1905 Fullagar 29/1561; R
I5 37 4o 37 1? F. lc I Yfil M l III JFHTFMHH 0 ms 3.887; 976 SHEET 1 INVENTOR. J. RODGER SHIELDS BYALEXANDER CARROLL ATTORNEY SHEU YATENTEU JUH 10 I975 BY 5 ARROLL ATTORNEY m 0; WWW v 0: N 4 6 mm mm Q 7 Z 8 R f 8 STATOR BLADE ASSEMBLY FOR TURBO MACHINES This is a division. of application Ser. No. 112.163 filed Feb. 3. 1971. now abandoned.
BACKGROUND OF THE INVENTION In some types of multistage axial flow turbo machines. the stator blades are fixedly mounted in the stator housing by locking the tangs. or journals. at the outer ends of the blades to the stator housing. In large high speed machines. the stator blades are subjected to forces of substantial magnitude tending to create a vibratory condition in the blades. To reduce such vibration. inner shroud rings have been fixedly secured to the inner ends of the fixed blades; for example. as shown in US. Pat. No. 3.269.701. assigned to the assignee herein.
In turbo machines for certain applications. it is desirable to mount at least one row of the stator blades for rotative adjustment about their lengthwise axis. To eliminate excessive vibration in the adjustable blades. it is necessary to provide a relatively close running fit between the blade journals and stator housing and the inner shroud ring. In view of the mounting of the blades for rotation. problems are encountered in the manufacture and assembly of the inner shroud rings to the blades to provide the proper support thereof. and to provide free adjustment of the blades under operating conditions.
This invention has as an object a stator blade assembly structure wherein the inner shroud ring is of simple one-piece construction. economical to manufacture and which is quickly and conveniently mounted on the inner ends of an arcuate series of stator blades.
SUMMARY OF THE INVENTION The stator blades of a stage are arranged in an arcuate series. which arrangement can be had by inserting the journals at the outer ends of the blades in apertures formed in the stator housing. and a one-piece shroud ring of arcuate configuration is formed with oversized apertures to receive projections at the inner ends of the circular series of blades. The ring is applied to the blades of the series by being contracted to reduce the chord dimension of the ring sufficient to clear the inner ends of the blades when the ring is inserted in the series. Upon release of the contraction force. the ring expands to its normal contour. moving the apertures of the ring over the journals at the inner ends of the blades. With the ring so positioned. in the arcuate series of stator blades. annular bearing members are in serted in the apertures and have a close running fit with the ends of the blades. The bearings are locked in the apertures.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic illustration showing a preferred embodiment of the invention wherein the blades of a stage of the machine are arranged in an arcuate series in the stator housing. and illustrating the inner shroud ring in contracted form positioned for insertion in the series of blades. the housing and shroud ring being illus' trated in sections.
FIG. 2 is a view similar to FIG. I showing the shroud ring inserted farther in the series of blades.
FIG. 3 is an enlarged view taken on line III-III of FIG. 2.
FIG. 4 is an enlarged sectional view of the inner shroud ring and blade journal structure shown in FIG. 3.
DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to the fragmentary sectional view of FIG. 3, the shaft structure ofthe turbo machine is designated 10, and has affixed to it a series of axially arranged discs II. Each disc 11 carries a circular series of rotor blades 12, there being a disc and series of blades 12 for each stage of the machine. The blades 12 are encircled by a stator housing 13 which conventionally consists of two semi-circular sections having side bosses l bolted together. FIGS. 1 and 2.
A circular series of stator blades 17 is mounted intermediate each series of spaced rotating blades 12. The blades 17 are provided at their outer ends with projections in the form of tangs 20. which extend outwardly through apertures formed in the stator housing 13.
The inner ends of the stator blades I7 are provided with projections or journals. which may be formed integral with the blades. or as shown in FIG. 4. may consist of annular collar members positioned on a tang portion 27, the outer end of which is headed over as shown at 28 to fixedly secure the collars 25 to the blades I7. Preferably the journals 25 are formed with radial flanges 26 abutting against the inner end of the blade.
A one-piece shroud ring section 30. shown in the pre ferred embodiment as being of semi-circular form. is provided with a series of apertures 33 spaced circumferentially along the ring comparable to the spacing of the inner ends of the blades I7. These apertures have a bore somewhat larger than the diameter of the collars 25 as indicated by the annular space 35. FIG. 4. encircling the periphery of the collar 25. These apertures are dimensioned so that upon applying a contracting force inwardly on the ends of the ring 30. as by rods 37 and turnbuckle 40. FIGS. I and 2. the ring is deflected to reduce the chordal dimension thereof sufficiently within its elastic limit. to permit the contracted ring to be inserted in the circular series. of blades 17. mounted in the half of the stator housing 13.
Referring to FIG. I, the aperture in the contracted ring 30, adjacent one end thereof. is placed over the journal of the blade I7 at the corresponding end of the series of blades. The ring is then rocked downwardly whereby the journals of the blades successively enter the apertures ofthe ring. In FIG. 2. the ring has been rocked downwardly to a position where the journal of the blade at the center of the series is about to enter the corresponding aperture in the ring. The turnbuckle 40 is then released permitting the ring to expand to normal contour. whereby the journals of the remaining blades 17 in the series enter the remaining apertures in the ring. The expanded ring being indicated by dotted outline 41, FIG. 2.
Annular bearing members are then inserted in the space between the periphery of each collar 25 and the bore of the aperture 33. The bearings have a snug fit with the bore in the apertures. and a close running fit with the collars 25. The bores of the apertures are formed with circular grooves to receive snap rings SI. FIG. 4. Thrust washers 53 are positioned between the snap ring and the bearings 50. Wlth this arrangement. the bearings are detachably interlocked with the ring 30, and a thrust structure is provided for the journaled stator blades 17. Because of the structure and mounting method described. the inner shroud rings 30 are economically produced by a turning operation. and are completed by the drilling and grooving of the apertures 33. The rings may be formed circular and subsequently split to provide the two integral semi-circular sections for use in each stage of the machine. This one-piece formation of the shroud ring greatly reduces the time and effort in the assembly of the shroud rings in the machine.
The stator housing 13, illustrated in FIGS. 1 and 2, may be the half section of the housing associated with the bottom half of the machine casing. After the stator blades 17 have been assembled in the stator housing for each stage. and the ring 30 attached to the inner ends of the blades. the rotor assembly is lowered into the machine.
The upper halfof the machine casing is then supplied with the stator blades. and the shroud rings 30 applied to those blades in like manner. That assembly is then inverted and placed upon the lower half of the casing and affixed thereto. It will be apparent that our inven' tion provides adequate support for the journaled stator blades. and also materially reduces the time and expense in the assembly of the machine.
It will be noted that the shroud ring assembly struc ture of our invention permits the shroud ring to be formed in two semi-circular sections which are manufactured at low cost and are easily and quickly assembled in the machine. in addition. the construction serving as the subject matter of this invention provides a more reliable structure'than in previous shroud ring constructions. as for example. the two-piece bolted sections adapted to clamp the inward projecting ends of the stator blades at opposite sides thereof as disclosed in U.S. Pat. No. 3.269.701.
While we have described a preferred embodiment of our invention. it is to be understood that the invention is not limited thereto. but may be otherwise embodied within the scope of the following claims.
We claim:
1. The method of assembling an arcuate shroud ring to the inner ends of an arcuate series of stator blades extending in a radial direction inwardly from a machine casing, the ring having apertures spaced apart circumferentially for receiving in registration therewith said blade ends, the method including contracting the shroud ring by applying a force thereto to reduce the diameter of the shroud ring to a diameter less than that described by the ends of the blades in the series whereby at least one blade receiving aperture in the ring is insertable into one of said blade ends,
inserting said one aperture into said one blade end.
and
relieving said contracting force to permit the shroud ring to expand whereby the remaining apertures move into receiving registration with the remaining blade ends in said series.
2. The method of claim 1 wherein said one blade end is carried on the last blade in said series.
3. The method of claim 2 wherein the shroud ring is semi-circular in form.

Claims (3)

1. The method of assembling an arcuate shroud ring to the inner ends of an arcuate series of stator blades extending in a radial direction inwardly from a machine casing, the ring having apertures spaced apart circumferentially for receiving in registration therewith said blade ends, the method including contracting the shroud ring by applying a force thereto to reduce the diameter of the shroud ring to a diameter less than that described by the ends of the blades in the series whereby at least one blade receiving aperture in the ring is insertable into one of said blade ends, inserting said one aperture into said one blade end, and relieving said contracting force to permit the shroud ring to expand whereby the remaining apertures move into receiving registration with the remaining blade ends in said series.
2. The method of claim 1 wherein said one blade end is carried on the last blade in said series.
3. The method of claim 2 wherein the shroud ring is semi-circular in form.
US335973A 1971-02-03 1973-02-26 Stator blade assembly for turbo machines Ceased US3887976A (en)

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Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3969805A (en) * 1974-12-23 1976-07-20 The Trane Company Method of constructing an axial flow fan
US3975816A (en) * 1974-12-10 1976-08-24 Ershig's, Inc. Method for making fiber reinforced resin tank forming mandrel
US4236399A (en) * 1978-10-02 1980-12-02 Williams Orlan G Method of forming a parabolic trough
EP0364726A1 (en) * 1988-10-14 1990-04-25 Westinghouse Electric Corporation Axial flow steam turbine
US5163809A (en) * 1991-04-29 1992-11-17 Pratt & Whitney Canada, Inc. Spiral wound containment ring
US6059523A (en) * 1998-04-20 2000-05-09 Pratt & Whitney Canada Inc. Containment system for containing blade burst
EP1422384A1 (en) * 2001-08-03 2004-05-26 Akita Fine Blanking Co., Ltd. METHOD OF MANUFACTURING COMPONENT MEMBER IN VGS TYPE TURBO CHARGER, COMPONENT MEMBER MANUFACTURED BY THE METHOD, EXHAUST GUIDE ASSEMBLY OF VGS TYPE TURBO CHARGER USING THE COMPONENT MEMBER, AND VGS TYPE TURBO CHARGER INCORPORATING THE EXHAUST GUIDE ASSEMBLY
US20080308094A1 (en) * 2006-02-03 2008-12-18 Johnston Glen Trough reflectors for solar energy collectors
US20120177484A1 (en) * 2011-01-07 2012-07-12 General Electric Company Elliptical Sealing System
EP2696043A1 (en) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Guide vane assembly and turbo engine
US20160215653A1 (en) * 2015-01-28 2016-07-28 United Technologies Corporation Method of assembling gas turbine engine section
US20200088049A1 (en) * 2018-09-18 2020-03-19 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
US10753393B2 (en) 2017-09-20 2020-08-25 Rolls-Royce Plc Bearing assembly

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US839243A (en) * 1906-06-04 1906-12-25 Wilkinson Turbine Company Turbine bucket-wheel.
US1158755A (en) * 1914-07-23 1915-11-02 Joseph Briggs Weaver Method of marking, punching, and assembling shroud-bands for turbine-blades.
US1621002A (en) * 1924-04-09 1927-03-15 Allis Chalmers Mfg Co Method of manufacturing turbines
US2856118A (en) * 1952-07-24 1958-10-14 Gen Motors Corp Blading assembly

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US839243A (en) * 1906-06-04 1906-12-25 Wilkinson Turbine Company Turbine bucket-wheel.
US1158755A (en) * 1914-07-23 1915-11-02 Joseph Briggs Weaver Method of marking, punching, and assembling shroud-bands for turbine-blades.
US1621002A (en) * 1924-04-09 1927-03-15 Allis Chalmers Mfg Co Method of manufacturing turbines
US2856118A (en) * 1952-07-24 1958-10-14 Gen Motors Corp Blading assembly

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US3975816A (en) * 1974-12-10 1976-08-24 Ershig's, Inc. Method for making fiber reinforced resin tank forming mandrel
US3969805A (en) * 1974-12-23 1976-07-20 The Trane Company Method of constructing an axial flow fan
US4236399A (en) * 1978-10-02 1980-12-02 Williams Orlan G Method of forming a parabolic trough
EP0364726A1 (en) * 1988-10-14 1990-04-25 Westinghouse Electric Corporation Axial flow steam turbine
US5163809A (en) * 1991-04-29 1992-11-17 Pratt & Whitney Canada, Inc. Spiral wound containment ring
US6059523A (en) * 1998-04-20 2000-05-09 Pratt & Whitney Canada Inc. Containment system for containing blade burst
EP1422384A4 (en) * 2001-08-03 2007-06-13 Akita Fine Blanking Co Ltd Method of manufacturing component member in vgs type turbo charger, component member manufactured by the method, exhaust guide assembly of vgs type turbo charger using the component member, and vgs type turbo charger incorporating the exhaust guide assembly
US20040231327A1 (en) * 2001-08-03 2004-11-25 Shinjiroh Ohishi Method of manufacturing component member in vgs type turbo charger, component member manufactured by the method, exhaust guide assembly of vgs type turbo charger using the component member, and vgs type turbo charger incorporating the exhaust guide assembly
EP1422384A1 (en) * 2001-08-03 2004-05-26 Akita Fine Blanking Co., Ltd. METHOD OF MANUFACTURING COMPONENT MEMBER IN VGS TYPE TURBO CHARGER, COMPONENT MEMBER MANUFACTURED BY THE METHOD, EXHAUST GUIDE ASSEMBLY OF VGS TYPE TURBO CHARGER USING THE COMPONENT MEMBER, AND VGS TYPE TURBO CHARGER INCORPORATING THE EXHAUST GUIDE ASSEMBLY
US20080308094A1 (en) * 2006-02-03 2008-12-18 Johnston Glen Trough reflectors for solar energy collectors
US20120177484A1 (en) * 2011-01-07 2012-07-12 General Electric Company Elliptical Sealing System
EP2696043A1 (en) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Guide vane assembly and turbo engine
US20160215653A1 (en) * 2015-01-28 2016-07-28 United Technologies Corporation Method of assembling gas turbine engine section
US9909457B2 (en) * 2015-01-28 2018-03-06 United Technologies Corporation Method of assembling gas turbine engine section
US10753393B2 (en) 2017-09-20 2020-08-25 Rolls-Royce Plc Bearing assembly
US20200088049A1 (en) * 2018-09-18 2020-03-19 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
US11028709B2 (en) * 2018-09-18 2021-06-08 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut

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