US2995294A - Stator casing and blade assembly - Google Patents

Stator casing and blade assembly Download PDF

Info

Publication number
US2995294A
US2995294A US736127A US73612758A US2995294A US 2995294 A US2995294 A US 2995294A US 736127 A US736127 A US 736127A US 73612758 A US73612758 A US 73612758A US 2995294 A US2995294 A US 2995294A
Authority
US
United States
Prior art keywords
casing
blades
blade
blade assembly
stator
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
US736127A
Inventor
Elmer P Warnken
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.)
Studebaker Packard Corp
Original Assignee
Studebaker Packard Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US472644A external-priority patent/US2857093A/en
Application filed by Studebaker Packard Corp filed Critical Studebaker Packard Corp
Priority to US736127A priority Critical patent/US2995294A/en
Application granted granted Critical
Publication of US2995294A publication Critical patent/US2995294A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • An object of this invention is to provide a stator casing and blade assembly which is simple and easy to construct and which is strong and durable.
  • a further object of this invention is to provide a stator casing which can be constructed without need for complex machining operations.
  • a further object of this invention is to provide a stator casing and blade assembly in which individual blades can readily be mounted and from which blades can readily be removed for servicing.
  • a further object of this invention is to provide a stator casing and blade assembly in which blades having wedgeshaped root end portions are received in slotted segmentshaped members which may be assembled or formed integrally with the casing, the wedge-shaped end of each blade being held firmly in the slot thereof.
  • a further object of this invention is to provide such an assembly in which the blades extend through segmental members disposed in apertures or slots in an outer casing member, the root ends being larger than the apertures, the root ends of the blades being clamped between the inner wall of the casing and said segmental members.
  • a further object of this invention is to provide a stator casing and blade assembly in which the casing itself is provided with apertures through which the blades extend,
  • the root ends of the blades being larger than the apertures and being firmly secured therein by an outer wrapping or & retaining web or strap embracing the casing and holding the blades firmly in position.
  • FIGURE 1 is a perspective view showing a half section of a casing for an axial flow compressor of an aircraft engine
  • FIG. 2 is an enlarged view in section taken on line II-II in FIG. 1 with stator blades mounted therein;
  • FIG. 3 is a perspective view partly in section showing a segment and blade assembly embodied in the casing section of FIG. 2;
  • FIG. 4 is a partial view in section taken on line IV--IV in FIG. 2;
  • FIG. 5 is a perspective view showing a portion of a stator casing including two half sections constructed in accordance with another embodiment of this invention.
  • FIG. 6 is an enlarged partial view in section taken on line VI-VI of FIG. 5 showing details of mounting the blades in the casing section;
  • FIG. 7 is a fragmentary plan view of a portion of the casing looking in the direction of the arrows VII--VII in FIG. 6;
  • FIG. 8 is a view in section taken along the line VIII-VIII in FIG. 6.
  • FIG. 1 is illustrated a half-section 10 of a casing ice of general frusto-conical shape provided with flanges 11 at the part line thereof (only one of which is shown) provided with bolt holes 11 for use in attaching the half-section 10 to another similar half-section to form a complete casing section.
  • flanges 12 and 13 are provided at opposite ends of the half-section for use in attaching it to adjacent casing sections of an axial flow compressor.
  • the inner wall of half-section 10 is provided with a plurality of spaced annular grooves 14.
  • Each groove 14 receives a segment 17 provided with a plurality of blades 18.
  • each blade 18 includes a main or airfoil portion 19 and a root end portion 21.
  • the root end portion 21 of each blade is of wedge shape, the sides of the wedge diverging from the airfoil portion 19 of the blade.
  • the segment 17 is provided with wedge-shaped apertures through which the blades are inserted and in which the portions 21 are received and retained.
  • the segment is provided with a series of threaded holes 23, in the threads of which a helical member 24 of the helicoil type is received.
  • the heli-coil 24 registers with the threads of a bolt 26.
  • the size of the heli-coil is exaggerated for clarity of showing.
  • the segments 17 are held in the grooves 14 by means of the bolts 26.
  • the bolts are received in metal bushings 26' located in the bolt holes in the casing 10, as shown.
  • the outer end 31 of the wedgeshaped root 21 of each blade projects outwardly of the segment17 a short distance and engages the base of the groove 14, so that when the bolts 26 are drawn tight, the root portions 21 are wedged firmly in position in the apertures 22 of segment 17.
  • the casing and the segments may be formed of metal or of resin-impregnated glass fabric. Since there is no undercutting at the grooves, the casing may be molded and requires little or no machining. Preferably the casing and the segments are formed of resin-impregnated fibre glass, or the like, and the blades may be formed of similar material, and all the major parts are molded to shape.
  • stator blades of a cantilever type are shown. However, if desired, the blades may be stayed at the inner ends by a support ring or shroud of the type which is common in axial flow compressors.
  • FIGS. 5-8 inclusive a section of a stator casing and blade assembly constructed in accordance with another embodiment of the invention.
  • the stator casing section of FIG. 5 includes two half-sections 36 and 37. The half-sections are held together by bolts 38 which extend through flanges 39 and 41 on the casing half-sections.
  • each half-section is provided with a plurality of apertures or slots 42.
  • the slots 42 are of wedge-shape in section as shown in FIG. 8.
  • Each of these slots can receive a blade 43 which may be similar in construction to one of the blades already described.
  • the blades project through the walls of the casing sections with the root ends of the blades being received in the openings 42 and a small portion of each root end extending outwardly of the casing.
  • Each strap includes an upper portion 44a and a lower portion 44b.
  • the ends of the upper and lower portions of each strap are bent outwardly to form tabs 46 and 47.
  • the tabs 46 and 47 are provided with aligned openings for receiving bolts 48 which draw the strips tightly against the wall of the casing and against the outer ends of the blades to hold the blades in position with the airfoil portions of. the blades projecting into the casing, as shown in FIGS. 6 and 8.
  • the stnaps are mounted on the casing section between lines of lugs 51 which hold the straps in alignment with the rows of slots 42.
  • the casing sections of the device illustrated in FIGS. -8 may be molded of resin-impregnated glass fabric, or the like, and the blades may be of similar construction. However, both the casing sections and the blades may be formed of other materials such as light strong metals, or the like, if preferred.
  • the wrapping strap may be stainless steel or other material of high tensile strength.
  • stator casing and blade assemblies illustrated in the drawings, and described above, are subject to structural modification without departing from the spirit and scope of the appended claims.
  • a stator casing and blade assembly for an axial flow compressor which comprises -a plurality of stator blades, each of said stator blades having an airfoil portion and a root end portion, the root end portion being of wedge shape with the wedge diverging from the airfoil portion, a hollow casing, an elongated blade-holding strip of segment-shape fitting inside of and substantially conforming with a portion of the interior of the casing and provided with a plurality of radially outward expanding wedgeshaped slots extending through the strip for receiving the root end portions of the blades, there being a section on the interior of the casing having an inwardly directed face complementary to an outer face of the blade-holding strip for receiving the blade-holding strip with the wide ends of the slots opposed to said face of the casing, the wide ends of the blades extending free of the outer face of the bladeholding strip, and means mounted in the casing and engaging the blade holding strip, for attaching the bladeholding strip to the casing with the wide ends of the root end portions of the blades engaging said
  • a stator casing and blade assembly for an axial flow compressor which comprises a plurality of stator blades, each of said blades having an airfoil portion and a root end portion, the root end portion being of wedgeshape with the wedge diverging from the airfoil portion, a plurality of hollow casing sections, a plurality of elongated blade-holding strips of segment-shape fitting inside of and substantially conforming with a portion of the interior of the casing sections, each of said blade-holding strips having radially outward expanding wedge-shaped slots extending through the strip for receiving the root end portions of the blades, there being inwardly directed faces on said casing sections complementary to outer faces of the blade-holding strips for receiving said bladeholding strips with the wide ends of the slots opposed to said faces of said casing sections, the wide ends of the root end portions of the blades extending free of the outer faces of the blade-holding strips, and means mounted in the casing sections and engageable with each blade holding strip for attaching the blade holding strips to the casing sections with the wide ends

Description

Aug. 8, 1961 E. P. WARNKEN 2,995,294
STATOR CASING AND BLADE ASSEMBLY Original Filed Dec. 2. 1954 4 Sheets-Sheet 1 Q INVENTOR.
ELMER R Maw/rm BY 9 7 1,514 W W Aug. 8, 1961 E. P. WARNKEN 2,995,294
STATOR CASING AND BLADE ASSEMBLY Original Filed Dec. 2. 1954 4 Sheets-Sheet 2 INVENTOR.
Aug. 8, 1961 E. P. WARNKEN 2,995,294
STATOR CASING AND BLADE ASSEMBLY Original Filed Dec. 2, 1954 4 Sheets-Sheet 3 INVEN TOR.
l E}. Aim 7'5? I? MRNKEN m wjd iab Aug. 8, 1961 E. P. WARNKEN 2,995,294
STATOR CASING AND BLADE ASSEMBLY Original Filed Dec. 2, 1954 4 Sheets-Sheet 4 INVENTOR. ELMER P. M/ARNKEN United States Patent 2,995,294 STATOR CASING AND BLADE ASSEMBLY Elmer P. Warnken, Cincinnati, Ohio, assignor, by mesne assignments, to Studebaker-Packard Corporation, South Bend, Ind., a corporation of Michigan Original application Dec. 2, 1954, Ser. No. 472,644, now
Patent No. 2,857,093, dated Oct. 21, 1958. Divided and this application May 19, 1958, Ser. No. 736,127
2 Claims. (Cl. 230-132) This invention relates to a stator casing and blade assembly for an axial flow compressor such as the compressor section of a jet aircraft engine, or the like. This is a division of my co-pending application Serial No. 472,644, filed December 2, 1954, now Patent No. 2,857,- 093.
An object of this invention is to provide a stator casing and blade assembly which is simple and easy to construct and which is strong and durable.
A further object of this invention is to provide a stator casing which can be constructed without need for complex machining operations.
A further object of this invention is to provide a stator casing and blade assembly in which individual blades can readily be mounted and from which blades can readily be removed for servicing.
A further object of this invention is to provide a stator casing and blade assembly in which blades having wedgeshaped root end portions are received in slotted segmentshaped members which may be assembled or formed integrally with the casing, the wedge-shaped end of each blade being held firmly in the slot thereof.
A further object of this invention is to provide such an assembly in which the blades extend through segmental members disposed in apertures or slots in an outer casing member, the root ends being larger than the apertures, the root ends of the blades being clamped between the inner wall of the casing and said segmental members.
A further object of this invention is to provide a stator casing and blade assembly in which the casing itself is provided with apertures through which the blades extend,
the root ends of the blades being larger than the apertures and being firmly secured therein by an outer wrapping or & retaining web or strap embracing the casing and holding the blades firmly in position.
The above and other objects and features of the invention will in part be apparent and will in part be obvious to those skilled in the art to which this invention pertains, from the following detailed description, and the drawings, in which:
FIGURE 1 is a perspective view showing a half section of a casing for an axial flow compressor of an aircraft engine;
FIG. 2 is an enlarged view in section taken on line II-II in FIG. 1 with stator blades mounted therein;
FIG. 3 is a perspective view partly in section showing a segment and blade assembly embodied in the casing section of FIG. 2;
FIG. 4 is a partial view in section taken on line IV--IV in FIG. 2;
FIG. 5 is a perspective view showing a portion of a stator casing including two half sections constructed in accordance with another embodiment of this invention;
FIG. 6 is an enlarged partial view in section taken on line VI-VI of FIG. 5 showing details of mounting the blades in the casing section;
FIG. 7 is a fragmentary plan view of a portion of the casing looking in the direction of the arrows VII--VII in FIG. 6; and
FIG. 8 is a view in section taken along the line VIII-VIII in FIG. 6.
In FIG. 1 is illustrated a half-section 10 of a casing ice of general frusto-conical shape provided with flanges 11 at the part line thereof (only one of which is shown) provided with bolt holes 11 for use in attaching the half-section 10 to another similar half-section to form a complete casing section. In addition, flanges 12 and 13 are provided at opposite ends of the half-section for use in attaching it to adjacent casing sections of an axial flow compressor.
As shown in FIG. 2., the inner wall of half-section 10 is provided with a plurality of spaced annular grooves 14. Each groove 14 receives a segment 17 provided with a plurality of blades 18.
A segment 17 with its complement of blades 18 is illustrated in FIG. 3. As there illustrated, each blade 18 includes a main or airfoil portion 19 and a root end portion 21. The root end portion 21 of each blade is of wedge shape, the sides of the wedge diverging from the airfoil portion 19 of the blade. The segment 17 is provided with wedge-shaped apertures through which the blades are inserted and in which the portions 21 are received and retained. In addition, the segment is provided with a series of threaded holes 23, in the threads of which a helical member 24 of the helicoil type is received. The heli-coil 24 registers with the threads of a bolt 26. In FIG. 4, the size of the heli-coil is exaggerated for clarity of showing.
As shown in FIG. 2, the segments 17 are held in the grooves 14 by means of the bolts 26. The bolts are received in metal bushings 26' located in the bolt holes in the casing 10, as shown.
As shown in FIG. 4, the outer end 31 of the wedgeshaped root 21 of each blade projects outwardly of the segment17 a short distance and engages the base of the groove 14, so that when the bolts 26 are drawn tight, the root portions 21 are wedged firmly in position in the apertures 22 of segment 17.
The casing and the segments may be formed of metal or of resin-impregnated glass fabric. Since there is no undercutting at the grooves, the casing may be molded and requires little or no machining. Preferably the casing and the segments are formed of resin-impregnated fibre glass, or the like, and the blades may be formed of similar material, and all the major parts are molded to shape.
In the device illustrated in FIGS. l-4, inclusive, stator blades of a cantilever type are shown. However, if desired, the blades may be stayed at the inner ends by a support ring or shroud of the type which is common in axial flow compressors.
In FIGS. 5-8 inclusive is shown a section of a stator casing and blade assembly constructed in accordance with another embodiment of the invention. The stator casing section of FIG. 5 includes two half- sections 36 and 37. The half-sections are held together by bolts 38 which extend through flanges 39 and 41 on the casing half-sections. As shown in FIGS. 5 and 6, each half-section is provided with a plurality of apertures or slots 42. The slots 42 are of wedge-shape in section as shown in FIG. 8. Each of these slots can receive a blade 43 which may be similar in construction to one of the blades already described. The blades project through the walls of the casing sections with the root ends of the blades being received in the openings 42 and a small portion of each root end extending outwardly of the casing.
The blades are held in place in the slots 42 by straps 44. Each strap includes an upper portion 44a and a lower portion 44b. The ends of the upper and lower portions of each strap are bent outwardly to form tabs 46 and 47. The tabs 46 and 47 are provided with aligned openings for receiving bolts 48 which draw the strips tightly against the wall of the casing and against the outer ends of the blades to hold the blades in position with the airfoil portions of. the blades projecting into the casing, as shown in FIGS. 6 and 8. The stnaps are mounted on the casing section between lines of lugs 51 which hold the straps in alignment with the rows of slots 42.
The casing sections of the device illustrated in FIGS. -8 may be molded of resin-impregnated glass fabric, or the like, and the blades may be of similar construction. However, both the casing sections and the blades may be formed of other materials such as light strong metals, or the like, if preferred. The wrapping strap may be stainless steel or other material of high tensile strength.
The stator casing and blade assemblies illustrated in the drawings, and described above, are subject to structural modification without departing from the spirit and scope of the appended claims.
Having described my invention, what I claim as new, and desire to secure by Letters Patent is:
1. A stator casing and blade assembly for an axial flow compressor which comprises -a plurality of stator blades, each of said stator blades having an airfoil portion and a root end portion, the root end portion being of wedge shape with the wedge diverging from the airfoil portion, a hollow casing, an elongated blade-holding strip of segment-shape fitting inside of and substantially conforming with a portion of the interior of the casing and provided with a plurality of radially outward expanding wedgeshaped slots extending through the strip for receiving the root end portions of the blades, there being a section on the interior of the casing having an inwardly directed face complementary to an outer face of the blade-holding strip for receiving the blade-holding strip with the wide ends of the slots opposed to said face of the casing, the wide ends of the blades extending free of the outer face of the bladeholding strip, and means mounted in the casing and engaging the blade holding strip, for attaching the bladeholding strip to the casing with the wide ends of the root end portions of the blades engaging said facing of the 4 casing to urge the root end portion of each blade firmly into the slot associated therewith and secure each blade to the blade-holding strip.
2. A stator casing and blade assembly for an axial flow compressor which comprises a plurality of stator blades, each of said blades having an airfoil portion and a root end portion, the root end portion being of wedgeshape with the wedge diverging from the airfoil portion, a plurality of hollow casing sections, a plurality of elongated blade-holding strips of segment-shape fitting inside of and substantially conforming with a portion of the interior of the casing sections, each of said blade-holding strips having radially outward expanding wedge-shaped slots extending through the strip for receiving the root end portions of the blades, there being inwardly directed faces on said casing sections complementary to outer faces of the blade-holding strips for receiving said bladeholding strips with the wide ends of the slots opposed to said faces of said casing sections, the wide ends of the root end portions of the blades extending free of the outer faces of the blade-holding strips, and means mounted in the casing sections and engageable with each blade holding strip for attaching the blade holding strips to the casing sections with the wide ends of the root end portions of the blades engaging said faces to urge the root end portion of each blade firmly into the slot associated therewith and secure each blade to one of the bladeholding strips.
References Cited in the tile of this patent UNITED STATES PATENTS 1,187,428 Homersham June 13, 1916 FOREIGN PATENTS 572,859 Great Britain Oct. 26, 1945 660,383 Great Britain Nov. 7, 1951 UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION Patent No. 2,995,29 August 8, 1961 iE lme r P. W arnken It is hereby certified that error appears in the above numbered patent requiring correction and that the said Letters Patent. should read as "corrected below.
Column 3, line 37, for "facing" read face Signed and sealed this 7th day of November 1961.
(SEAL) Attest:
ERNEST W. SWIDER DAVID L. LADD Attesting Officer Commissioner of Patents USCOMM-DC
US736127A 1954-12-02 1958-05-19 Stator casing and blade assembly Expired - Lifetime US2995294A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US736127A US2995294A (en) 1954-12-02 1958-05-19 Stator casing and blade assembly

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US472644A US2857093A (en) 1954-12-02 1954-12-02 Stator casing and blade assembly
US736127A US2995294A (en) 1954-12-02 1958-05-19 Stator casing and blade assembly

Publications (1)

Publication Number Publication Date
US2995294A true US2995294A (en) 1961-08-08

Family

ID=27043847

Family Applications (1)

Application Number Title Priority Date Filing Date
US736127A Expired - Lifetime US2995294A (en) 1954-12-02 1958-05-19 Stator casing and blade assembly

Country Status (1)

Country Link
US (1) US2995294A (en)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3219263A (en) * 1962-01-30 1965-11-23 Rolls Royce Compressor for a gas turbine engine
US3242672A (en) * 1962-06-28 1966-03-29 Rolls Royce Intake cover for a gas turbine engine
US3339833A (en) * 1963-12-04 1967-09-05 Rolls Royce Axial fluid flow machine such as a compressor or turbine
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
US3997280A (en) * 1974-06-21 1976-12-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Stators of axial turbomachines
US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing
US4500255A (en) * 1981-04-24 1985-02-19 United States Of America As Represented By The Secretary Of The Air Force Spacer structure
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
FR2642113A1 (en) * 1989-01-20 1990-07-27 Rolls Royce Plc Method for manufacturing a set of fixed-blading fins for an axial-flow compressor and set of fins obtained by this method
FR2664944A1 (en) * 1990-07-18 1992-01-24 Snecma Compressor formed particularly of diffusers in the shape of a ring and method for mounting this compressor
US5167488A (en) * 1991-07-03 1992-12-01 General Electric Company Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
US5472315A (en) * 1993-11-09 1995-12-05 Sundstrand Corporation Abradable coating in a gas turbine engine
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
WO2005066462A1 (en) * 2004-01-09 2005-07-21 Mtu Aero Engines Gmbh Device for suspending guide blades
DE102004005237B4 (en) * 2004-02-03 2007-03-01 Mtu Aero Engines Gmbh Guide vane grille of a gas turbine
US20100322763A1 (en) * 2009-06-18 2010-12-23 Techspace Aero S.A. Method for manufacturing vanes integrated into a ring and rectifier by the method
US20110243752A1 (en) * 2010-04-02 2011-10-06 Techspace Aero S.A. Method for manufacturing a rectifier
US20120128497A1 (en) * 2010-11-24 2012-05-24 Rowley Hope C Turbine engine compressor stator
US8206086B1 (en) * 2008-04-22 2012-06-26 Florida Turbine Technologies, Inc. Turbofan hybrid metallic and plastic inlet case
CN102619575A (en) * 2011-01-27 2012-08-01 通用电气公司 Turbomachine service assembly
US20180283397A1 (en) * 2017-04-04 2018-10-04 General Electric Company Turbine engine containment assembly and method for manufacturing the same

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1187428A (en) * 1914-06-01 1916-06-13 Thomas Henry Collett Homersham Centrifugal blower and like machine.
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
GB660383A (en) * 1949-02-23 1951-11-07 Winnett Boyd Blade mounting for axial-flow compressors and the like

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1187428A (en) * 1914-06-01 1916-06-13 Thomas Henry Collett Homersham Centrifugal blower and like machine.
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
GB660383A (en) * 1949-02-23 1951-11-07 Winnett Boyd Blade mounting for axial-flow compressors and the like

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3219263A (en) * 1962-01-30 1965-11-23 Rolls Royce Compressor for a gas turbine engine
US3242672A (en) * 1962-06-28 1966-03-29 Rolls Royce Intake cover for a gas turbine engine
US3339833A (en) * 1963-12-04 1967-09-05 Rolls Royce Axial fluid flow machine such as a compressor or turbine
US3997280A (en) * 1974-06-21 1976-12-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Stators of axial turbomachines
US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing
US3985465A (en) * 1975-06-25 1976-10-12 United Technologies Corporation Turbomachine with removable stator vane
US4500255A (en) * 1981-04-24 1985-02-19 United States Of America As Represented By The Secretary Of The Air Force Spacer structure
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
FR2642113A1 (en) * 1989-01-20 1990-07-27 Rolls Royce Plc Method for manufacturing a set of fixed-blading fins for an axial-flow compressor and set of fins obtained by this method
FR2664944A1 (en) * 1990-07-18 1992-01-24 Snecma Compressor formed particularly of diffusers in the shape of a ring and method for mounting this compressor
US5167488A (en) * 1991-07-03 1992-12-01 General Electric Company Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments
US5472315A (en) * 1993-11-09 1995-12-05 Sundstrand Corporation Abradable coating in a gas turbine engine
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
WO2005066462A1 (en) * 2004-01-09 2005-07-21 Mtu Aero Engines Gmbh Device for suspending guide blades
US20080292457A1 (en) * 2004-01-09 2008-11-27 Mtu Aero Engines Gmbh Device for Suspending Guide Blades
US8591182B2 (en) 2004-01-09 2013-11-26 Mtu Aero Engines Gmbh Device for suspending guide blades
DE102004005237B4 (en) * 2004-02-03 2007-03-01 Mtu Aero Engines Gmbh Guide vane grille of a gas turbine
US8206086B1 (en) * 2008-04-22 2012-06-26 Florida Turbine Technologies, Inc. Turbofan hybrid metallic and plastic inlet case
US8414259B2 (en) * 2009-06-18 2013-04-09 Techspace Aero S.A. Method for manufacturing vanes integrated into a ring and rectifier obtained by the method
US20100322763A1 (en) * 2009-06-18 2010-12-23 Techspace Aero S.A. Method for manufacturing vanes integrated into a ring and rectifier by the method
US20110243752A1 (en) * 2010-04-02 2011-10-06 Techspace Aero S.A. Method for manufacturing a rectifier
US8807933B2 (en) * 2010-04-02 2014-08-19 Techspace Aero S.A. Method for manufacturing a rectifier
US20120128497A1 (en) * 2010-11-24 2012-05-24 Rowley Hope C Turbine engine compressor stator
US9181814B2 (en) * 2010-11-24 2015-11-10 United Technology Corporation Turbine engine compressor stator
US20120195746A1 (en) * 2011-01-27 2012-08-02 General Electric Company Turbomachine service assembly
CN102619575A (en) * 2011-01-27 2012-08-01 通用电气公司 Turbomachine service assembly
US20180283397A1 (en) * 2017-04-04 2018-10-04 General Electric Company Turbine engine containment assembly and method for manufacturing the same
US10815804B2 (en) * 2017-04-04 2020-10-27 General Electric Company Turbine engine containment assembly and method for manufacturing the same

Similar Documents

Publication Publication Date Title
US2995294A (en) Stator casing and blade assembly
US2857093A (en) Stator casing and blade assembly
US3294364A (en) Rotor assembly
US2834537A (en) Compressor stator structure
US2994507A (en) Blade locking structure
US3356339A (en) Turbine rotor
US2999668A (en) Self-balanced rotor blade
US2914300A (en) Nozzle vane support for turbines
US3836282A (en) Stator vane support and construction thereof
US3126149A (en) Foamed aluminum honeycomb motor
US1362074A (en) Turbine
US3104091A (en) Turbines
GB996729A (en) Improvements relating to turbines and compressors
GB1008526A (en) Axial flow bladed rotor, e.g. for a turbine
GB1395957A (en) Fluid flow machines and rotors therefor
GB1259750A (en) Rotor for a fluid flow machine
US3339833A (en) Axial fluid flow machine such as a compressor or turbine
US3155395A (en) Shaft packing assembly
US3290004A (en) Device for damping vibration of long steam-turbine blades
US2906495A (en) Turbine blade with corrugated strut
US3503616A (en) Eccentric bushing for gland case keys
GB856599A (en) Improvements relating to axial-flow compressors
US2543355A (en) Stator for axial compressors
GB885951A (en) Arrangement for withdrawing cooling air from the compressor of a turbine engine
US3367630A (en) Continuous shroud structure