US3000552A - Compressor vane mounting - Google Patents

Compressor vane mounting Download PDF

Info

Publication number
US3000552A
US3000552A US660498A US66049857A US3000552A US 3000552 A US3000552 A US 3000552A US 660498 A US660498 A US 660498A US 66049857 A US66049857 A US 66049857A US 3000552 A US3000552 A US 3000552A
Authority
US
United States
Prior art keywords
rotor
shroud
case
vane
rings
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
US660498A
Inventor
Jr Lewis Cooper
Robert B Koschmann
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.)
Motors Liquidation Co
Original Assignee
General Motors 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
Application filed by General Motors Corp filed Critical General Motors Corp
Priority to US660498A priority Critical patent/US3000552A/en
Priority claimed from GB3907058A external-priority patent/GB850346A/en
Application granted granted Critical
Publication of US3000552A publication Critical patent/US3000552A/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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

  • FIGURE 1 is a fragmentary sectional view of a portion of an axial-flow compressor, taken on a plane containing the axis thereof.
  • FIGURE 2 is a cross-sectional view of the case and rotor shroud, taken on the plane indicated by the line 2- -2 in FIGURE 1.
  • FIGURE 3 is an enlarged view of a portion of FIG- URE 1.
  • the axial-flow compressor illustrated comprises a case of circular cross-section formed by two semi-cylindrical sections 11 and 12 suitably secured together when the compressor is assembled, by'means immaterial to this invention, at the split lines 13.
  • Successive stator vane rings 14, between which are rotor vane shrouds 16, are mounted in the interior of the case.
  • the rings 14 and shrouds 16 are in semi-circular segments meeting at the plane of the split line. The segments are fixed to the sections of the case so that each half of the stator is a complete assembly before the halves are united.
  • Rotor wheels 17 including flanges 18 are abutted to form a drum-type rotor, each wheel mounting a row of rotor blades 19.
  • the rotor blades have roots 21 inserted in axial dovetail slots 22 in the wheels and retained in the slots by an expanding split ring 23 engaging in a circumferential groove 24 in the inner surface of the Groove 24 cuts through the base of slots 22, and the ring 23 engages in slots 26 across the bottoms of the blade dovetails.
  • the right-hand wheel 17 in FIGURE 1 is seetioned at the rim between the blade slots, the left-hand Wheel at the blade slot.
  • the rotor structure may, however, be of any suitable character, as this invention is directed to the stator.
  • Each stator vane segment ring 14 includes a hat section outer shroud 27, radial vanes 28, a channel section inner shroud 29, and a labyrinth seal member 31 fixed to the inner shroud and cooperating with seal ridges 32 on the flange 18. These parts may be brazed together.
  • the case It is provided with ribs 33 on its inner surface. These ribs are accurately machined on their inner surface and one side surface. The flanges 34 of the outer vane shrouds 27 rest against the inner surfaces of adjacent ribs, thus precisely locating the vane ring radially and holding it accurately circular.
  • Each rotor shroud segment 16 comprises a channel section 35 with preferably five blocks 36 brazed into the channel. These blocks are rectangular and are dimensioned for a close fit between machined side faces of adjacent ribs 33 so as to located the shroud 16 axially of the compressor. Shoulders 37 on the blocks are aligned with the outer edge of the channel. These shoulders and the edge of the channel bear outwardly against flanges 34 to hold shrouds 27 against ribs 33.
  • Each block 36 is drilled and tapped to receive a cap screw 38 which extends through a hole 39 in the case.
  • the five screws 38 hold each segment 16 outwardly Patented Sept. 19, 1961 "ice .. accurately concentric with the case.
  • Ribs 33 provide good support at each edge of the.
  • each rotor shroud has a layer 41.
  • stator vane rings are laid in place, the rotor shrouds are laid over them, and the cap screws are inserted.
  • the rotor is mounted in one section, the other section is put in place, and the sections are joined by a suitable connection along the split line.
  • a stator structure for an axial-flow turbomachine comprising, in combination, a longitudinally split case section of circular arc cross-section having circular arc circumferential ribs on its inner surface, a plurality of stator vane ring segments providing stages of stator blading, each vane ring segment including an outer shroud bearing against the case only at the radially inner surface of the case ribs, rotor vane shroud segments mounted between the stator vane outer shrouds and bearing against the radially inner surface of the stator vane outer shroud, the rotor vane shroud segments including parts fitting between adjacent ribs and locating the rotor vane shroud segments axially of the case section, the edges of the stator vane outer shrouds engaging the said parts of adjacent rotor vane shroud segments to locate the vane ring segments axially of the case section, and means removably connected to the rotor vane shroud segments and case section holding the rotor vane sh
  • a stator structure for an axial-flow turbomachine comprising, in combination, a longitudinally split case section of circular arc cross-section having circular arc circumferential ribs on its inner surface, a plurality of stator vane ring segments providing stages of stator blading, each vane ring segment including an outer shroud of hat section, the flanges of the outer shroud bearing against the case only at the radially inner surface of the case ribs, rotor vane shroud segments mounted between the stator vane outer shrouds and bearing against the radially inner surface of the stator vane outer shroud flanges, the rotor vane shroud segments including parts fitting between adjacent ribs and locating the rotor vane shroud segments axially of the case section, the edges of the stator vane outer shrouds engaging the said parts of adjacent rotor vane shroud segments to locate the vane ring segments axially of the case section, and tension members remoyably
  • An axial-flow turbomachine stator comprising an annular case with circumferential ribs on the radially inner surface thereof and radial grooves between the ribs; stator vane rings having marginal portions bearing against the radially inner surface of the ribs, rotor shroud rings bearing against the radially inner surface of the said marginal portions of adjacent stator vane rings, and having parts extending radially intovsaid grooves and engaging between the ribs to locate the rotor shroud rings axially of the case, the edges of the vane rings bearing against the said parts of adjacent rotor shroud rings to locate the stator vane rings axially of the case, and means connected to the case and the rotor shroud rings holding the rotor shroud rings radially outwardly against the said marginal portions and thereby holding the stator vane rings against the case.
  • An axial-flow turbomachine stator comprising an annular case with circumferential ribsvon the radially inner surface thereof and radial grooves between the ribs; stator vane rings having axially-extending marginal portions bearing against the case only at the radially inner surface of the ribs, rotor shroud rings bearing against the radially inner surface of the said marginal portions of adjacent stator vane rings and having parts extending radially into said grooves and engaging between the ribs to locate the rotor shroud rings axially of the case, the edges of the vane rings bearing against the said parts of adjacent rotor shroud rings to locate the stator vane rings axially of the case, and means connected to the case and the rotor shroud rings holding the rotor shroud rings radially outwardly against the, said marginal portions and thereby holding the stator vane rings against the case.
  • An axial-flow turbomachine stator comprising an annular case with circumferential ribs on the radially inner surface thereof and radial grooves" between the ribs; stator vane rings bridging alternate grooves and having axially-extending marginal portions bearing against the case only at the radially inner surface of the ribs, rotor shroud rings bearing against the radially inner. surface of the said marginal portions of, adjacent stator vane ringsand having parts extending radially into alternate ones of the said grooves and engaging between the ribs.
  • stator vane rings axially of the case
  • edges of the stator vane rings bearingagainst the said parts of, adjacent rotor shroud rings to locate the stator vane rings axially of the case
  • means removably connected to the case and the rotor shroud rings holding the rotor shroud rings radially outwardly against the said marginal portions and thereby holding the stator vane rings'against" the case.

Landscapes

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

Description

Sept- 19, 1961 L. COOPER, JR., ETAL 3,000,552
COMPRESSOR VANE MOUNTING X M24 ,1? Jama 147 TURMEY I IN VENT ORS lea/256% 57, BY fiafi/ .s'a
3,000,552 COMPRESSOR VANE MOUNTING Lewis Cooper, Jr., and Robert B. Koschmann, Indianapolis, Ind, assignors to General Motors Corporation,
Detroit, Mich., a corporation of Delaware Filed May 28, 1957, Ser. No. 660,498 Claims. (Cl. 230-132) Our invention relates to stator constructions of turbomachines such as axial-flow compressors. It provides a structurally simple, readily assembled, and accurate stator structure.
The nature of the invention and the advantages thereof will be apparent to those skilled in the art from the succeeding detailed description of the preferred embodiment of the invention and the accompanying drawings thereof. FIGURE 1 is a fragmentary sectional view of a portion of an axial-flow compressor, taken on a plane containing the axis thereof.
' FIGURE 2 is a cross-sectional view of the case and rotor shroud, taken on the plane indicated by the line 2- -2 in FIGURE 1.
FIGURE 3 is an enlarged view of a portion of FIG- URE 1.
The axial-flow compressor illustrated comprises a case of circular cross-section formed by two semi-cylindrical sections 11 and 12 suitably secured together when the compressor is assembled, by'means immaterial to this invention, at the split lines 13. Successive stator vane rings 14, between which are rotor vane shrouds 16, are mounted in the interior of the case. The rings 14 and shrouds 16 are in semi-circular segments meeting at the plane of the split line. The segments are fixed to the sections of the case so that each half of the stator is a complete assembly before the halves are united.
Rotor wheels 17 including flanges 18 are abutted to form a drum-type rotor, each wheel mounting a row of rotor blades 19. The rotor blades have roots 21 inserted in axial dovetail slots 22 in the wheels and retained in the slots by an expanding split ring 23 engaging in a circumferential groove 24 in the inner surface of the Groove 24 cuts through the base of slots 22, and the ring 23 engages in slots 26 across the bottoms of the blade dovetails. The right-hand wheel 17 in FIGURE 1 is seetioned at the rim between the blade slots, the left-hand Wheel at the blade slot. The rotor structure may, however, be of any suitable character, as this invention is directed to the stator.
Each stator vane segment ring 14 includes a hat section outer shroud 27, radial vanes 28, a channel section inner shroud 29, and a labyrinth seal member 31 fixed to the inner shroud and cooperating with seal ridges 32 on the flange 18. These parts may be brazed together.
The case It) is provided with ribs 33 on its inner surface. These ribs are accurately machined on their inner surface and one side surface. The flanges 34 of the outer vane shrouds 27 rest against the inner surfaces of adjacent ribs, thus precisely locating the vane ring radially and holding it accurately circular.
Each rotor shroud segment 16 comprises a channel section 35 with preferably five blocks 36 brazed into the channel. These blocks are rectangular and are dimensioned for a close fit between machined side faces of adjacent ribs 33 so as to located the shroud 16 axially of the compressor. Shoulders 37 on the blocks are aligned with the outer edge of the channel. These shoulders and the edge of the channel bear outwardly against flanges 34 to hold shrouds 27 against ribs 33.
Each block 36 is drilled and tapped to receive a cap screw 38 which extends through a hole 39 in the case. The five screws 38 hold each segment 16 outwardly Patented Sept. 19, 1961 "ice .. accurately concentric with the case.
' of silver applied to it, which'is soft and thus may be:
cut away by the tips of blades 19 if there is any inter-- The edges of flanges 34 engage the blocks 36 at each side, thus accurately locating the vane ring axially of the case. Ribs 33 provide good support at each edge of the.
shroud 27.
The inner surface of each rotor shroud has a layer 41.
ference. This makes possible an extremely close clearance between blade tips and the shroud, improving com-.
pressor efiiciency. The clearance is greatly exaggerated in the drawings for clarity.
Assembly and disassembly of the stator is 'very easy, and accurate alignment of the parts is assured. The stator vane rings are laid in place, the rotor shrouds are laid over them, and the cap screws are inserted. When each section of the stator is assembled, the rotor is mounted in one section, the other section is put in place, and the sections are joined by a suitable connection along the split line. j
The advantages of the invention in providing a strong; accurately aligned, readily machined and assembled, and light weight stator structure will be apparent.
The invention is not to be considered as limited by the detailed description of the preferred embodiment thereof, as many modifications may be made by the exercise of skill in the art.
1. A stator structure for an axial-flow turbomachine comprising, in combination, a longitudinally split case section of circular arc cross-section having circular arc circumferential ribs on its inner surface, a plurality of stator vane ring segments providing stages of stator blading, each vane ring segment including an outer shroud bearing against the case only at the radially inner surface of the case ribs, rotor vane shroud segments mounted between the stator vane outer shrouds and bearing against the radially inner surface of the stator vane outer shroud, the rotor vane shroud segments including parts fitting between adjacent ribs and locating the rotor vane shroud segments axially of the case section, the edges of the stator vane outer shrouds engaging the said parts of adjacent rotor vane shroud segments to locate the vane ring segments axially of the case section, and means removably connected to the rotor vane shroud segments and case section holding the rotor vane shroud segments against the stator vane outer shroud.
2. A stator structure for an axial-flow turbomachine comprising, in combination, a longitudinally split case section of circular arc cross-section having circular arc circumferential ribs on its inner surface, a plurality of stator vane ring segments providing stages of stator blading, each vane ring segment including an outer shroud of hat section, the flanges of the outer shroud bearing against the case only at the radially inner surface of the case ribs, rotor vane shroud segments mounted between the stator vane outer shrouds and bearing against the radially inner surface of the stator vane outer shroud flanges, the rotor vane shroud segments including parts fitting between adjacent ribs and locating the rotor vane shroud segments axially of the case section, the edges of the stator vane outer shrouds engaging the said parts of adjacent rotor vane shroud segments to locate the vane ring segments axially of the case section, and tension members remoyably connected to the rotor vane shroud segments and case section holding the rotor vane shroud segments against the stator vane outer shroud flanges.
3. An axial-flow turbomachine stator comprising an annular case with circumferential ribs on the radially inner surface thereof and radial grooves between the ribs; stator vane rings having marginal portions bearing against the radially inner surface of the ribs, rotor shroud rings bearing against the radially inner surface of the said marginal portions of adjacent stator vane rings, and having parts extending radially intovsaid grooves and engaging between the ribs to locate the rotor shroud rings axially of the case, the edges of the vane rings bearing against the said parts of adjacent rotor shroud rings to locate the stator vane rings axially of the case, and means connected to the case and the rotor shroud rings holding the rotor shroud rings radially outwardly against the said marginal portions and thereby holding the stator vane rings against the case.
p 4. An axial-flow turbomachine stator comprising an annular case with circumferential ribsvon the radially inner surface thereof and radial grooves between the ribs; stator vane rings having axially-extending marginal portions bearing against the case only at the radially inner surface of the ribs, rotor shroud rings bearing against the radially inner surface of the said marginal portions of adjacent stator vane rings and having parts extending radially into said grooves and engaging between the ribs to locate the rotor shroud rings axially of the case, the edges of the vane rings bearing against the said parts of adjacent rotor shroud rings to locate the stator vane rings axially of the case, and means connected to the case and the rotor shroud rings holding the rotor shroud rings radially outwardly against the, said marginal portions and thereby holding the stator vane rings against the case.
5. An axial-flow turbomachine stator comprising an annular case with circumferential ribs on the radially inner surface thereof and radial grooves" between the ribs; stator vane rings bridging alternate grooves and having axially-extending marginal portions bearing against the case only at the radially inner surface of the ribs, rotor shroud rings bearing against the radially inner. surface of the said marginal portions of, adjacent stator vane ringsand having parts extending radially into alternate ones of the said grooves and engaging between the ribs. to locate the rotor shroud rings axially of the case, the edges of the stator vane rings bearingagainst the said parts of, adjacent rotor shroud rings to locate the stator vane rings axially of the case, and means removably connected to the case and the rotor shroud rings holding the rotor shroud rings radially outwardly against the said marginal portions and thereby holding the stator vane rings'against" the case.
References, Cited in. the file of this, patent UNITED STATES PATENTS n Me.- r-W
US660498A 1957-05-28 1957-05-28 Compressor vane mounting Expired - Lifetime US3000552A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US660498A US3000552A (en) 1957-05-28 1957-05-28 Compressor vane mounting

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US660498A US3000552A (en) 1957-05-28 1957-05-28 Compressor vane mounting
GB3907058A GB850346A (en) 1958-12-03 1958-12-03 Compressor or turbine stator

Publications (1)

Publication Number Publication Date
US3000552A true US3000552A (en) 1961-09-19

Family

ID=26263997

Family Applications (1)

Application Number Title Priority Date Filing Date
US660498A Expired - Lifetime US3000552A (en) 1957-05-28 1957-05-28 Compressor vane mounting

Country Status (1)

Country Link
US (1) US3000552A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
FR2535795A1 (en) * 1982-11-08 1984-05-11 Snecma AXIS COMPRESSOR STATORIC AUB SUSPENSION DEVICE FOR ACTIVE CONTROL OF GAMES BETWEEN ROTOR AND STATOR
FR2660362A1 (en) * 1990-04-03 1991-10-04 Gen Electric STRUCTURE FOR FIXING THE EXTERIOR EXTERMENTS OF THE BLADES OF A TURBINE.
US5501573A (en) * 1993-01-29 1996-03-26 Steam Specialties, Inc. Segmented seal assembly and method for retrofitting the same to turbines and the like
EP1455055A1 (en) * 2003-03-06 2004-09-08 Snecma Moteurs Turbomachine with cooled shroud segments
US20090053043A1 (en) * 2007-08-16 2009-02-26 Moon Francis R Attachment interface for a gas turbine engine composite duct structure
US20160201495A1 (en) * 2013-08-09 2016-07-14 Siemens Aktiengesellschaft Gas turbine and mounting method
US10508561B2 (en) * 2015-10-14 2019-12-17 Rolls-Royce Plc Shroud assembly for a gas turbine engine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction
FR1013114A (en) * 1949-02-23 1952-07-23 Canadian Patents Dev Blade mounting device for rotary force transformation machines
US2623728A (en) * 1945-01-16 1952-12-30 Power Jets Res & Dev Ltd Mounting of blades in compressors, turbines, and the like
GB689270A (en) * 1949-12-13 1953-03-25 Rateau Soc Improvements in axial flow turbines or compressors
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
GB710300A (en) * 1950-12-02 1954-06-09 Francis Henry Keast Axial flow compressor
US2722373A (en) * 1951-02-06 1955-11-01 United Aircraft Corp Compressor casing and stator assembly
US2763462A (en) * 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2766963A (en) * 1952-11-01 1956-10-16 Gen Motors Corp Turbine stator assembly

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction
US2623728A (en) * 1945-01-16 1952-12-30 Power Jets Res & Dev Ltd Mounting of blades in compressors, turbines, and the like
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
FR1013114A (en) * 1949-02-23 1952-07-23 Canadian Patents Dev Blade mounting device for rotary force transformation machines
GB689270A (en) * 1949-12-13 1953-03-25 Rateau Soc Improvements in axial flow turbines or compressors
US2763462A (en) * 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
GB710300A (en) * 1950-12-02 1954-06-09 Francis Henry Keast Axial flow compressor
US2722373A (en) * 1951-02-06 1955-11-01 United Aircraft Corp Compressor casing and stator assembly
US2766963A (en) * 1952-11-01 1956-10-16 Gen Motors Corp Turbine stator assembly

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
FR2535795A1 (en) * 1982-11-08 1984-05-11 Snecma AXIS COMPRESSOR STATORIC AUB SUSPENSION DEVICE FOR ACTIVE CONTROL OF GAMES BETWEEN ROTOR AND STATOR
EP0110757A1 (en) * 1982-11-08 1984-06-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Axial compressor stator blade fixing device for the active control of the play between rotor and stator
US4543039A (en) * 1982-11-08 1985-09-24 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator assembly for an axial compressor
FR2660362A1 (en) * 1990-04-03 1991-10-04 Gen Electric STRUCTURE FOR FIXING THE EXTERIOR EXTERMENTS OF THE BLADES OF A TURBINE.
US5501573A (en) * 1993-01-29 1996-03-26 Steam Specialties, Inc. Segmented seal assembly and method for retrofitting the same to turbines and the like
EP1455055A1 (en) * 2003-03-06 2004-09-08 Snecma Moteurs Turbomachine with cooled shroud segments
FR2852053A1 (en) * 2003-03-06 2004-09-10 Snecma Moteurs HIGH PRESSURE TURBINE FOR TURBOMACHINE
US20040219009A1 (en) * 2003-03-06 2004-11-04 Snecma Moteurs Turbomachine with cooled ring segments
US7011493B2 (en) 2003-03-06 2006-03-14 Snecma Moteurs Turbomachine with cooled ring segments
US20090053043A1 (en) * 2007-08-16 2009-02-26 Moon Francis R Attachment interface for a gas turbine engine composite duct structure
US8206102B2 (en) * 2007-08-16 2012-06-26 United Technologies Corporation Attachment interface for a gas turbine engine composite duct structure
US8596972B2 (en) 2007-08-16 2013-12-03 United Technologies Corporation Attachment interface for a gas turbine engine composite duct structure
US20160201495A1 (en) * 2013-08-09 2016-07-14 Siemens Aktiengesellschaft Gas turbine and mounting method
US10508561B2 (en) * 2015-10-14 2019-12-17 Rolls-Royce Plc Shroud assembly for a gas turbine engine

Similar Documents

Publication Publication Date Title
US3056583A (en) Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3295825A (en) Multi-stage turbine rotor
US3023998A (en) Rotor blade retaining device
GB779059A (en) Improvements in or relating to axial-flow fluid machines, for example compressors orturbines of gas-turbine engines
US2640679A (en) Turbine or compressor stator ring
GB617475A (en) Improvements relating to gas-turbine engines
US2738126A (en) Construction of compressor rotors
GB804922A (en) Improvements in or relating to axial-flow fluid machines for example compressors andturbines
GB715145A (en) Improvements in or relating to stator constructions for compressors
US2807434A (en) Turbine rotor assembly
US3000552A (en) Compressor vane mounting
US3335483A (en) Method of manufacturing a stator assembly for turbomachines
GB868848A (en) Segmental stator vane ring for a compressor or turbine
US2645413A (en) Stator for multistage axial compressors
US3248081A (en) Axial locating means for airfoils
GB1528421A (en) Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance
GB1217275A (en) Gas turbine engine axial flow multi-stage compressor
GB831412A (en) Improvements relating to axial-flow turbines
US3319930A (en) Stator assembly for turbomachines
US2543355A (en) Stator for axial compressors
US3024968A (en) Stator construction for multi-stage axial-flow compressor
US2833463A (en) Stator construction for axial flow compressor
GB867759A (en) Stator vane assemblies for axial-flow compressors or turbines
US3367630A (en) Continuous shroud structure
GB790280A (en) Gas turbine engines having a multiple-stage turbine