US20090191053A1 - Diaphragm and blades for turbomachinery - Google Patents

Diaphragm and blades for turbomachinery Download PDF

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Publication number
US20090191053A1
US20090191053A1 US11/902,642 US90264207A US2009191053A1 US 20090191053 A1 US20090191053 A1 US 20090191053A1 US 90264207 A US90264207 A US 90264207A US 2009191053 A1 US2009191053 A1 US 2009191053A1
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United States
Prior art keywords
portions
blades
diaphragm
blade
contact
Prior art date
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Abandoned
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US11/902,642
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English (en)
Inventor
Richard Martin Bridge
Philip David Hemsley
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General Electric Technology GmbH
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Alstom Technology AG
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Assigned to ALSTOM TECHNOLOGY LTD. reassignment ALSTOM TECHNOLOGY LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HEMSLEY, PHILIP DAVID, BRIDGE, RICHARD MARTIN
Publication of US20090191053A1 publication Critical patent/US20090191053A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/00—Geometry
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • Exemplary embodiments relate to the arrangement of turbine blades to form a turbine diaphragm of fixed blades that can operate at high temperatures and that results in a reduction in working fluid leakage in turbines caused by distortion of the blade rows due to changes in the operating temperature.
  • Steam turbines convert the energy in steam firstly into mechanical energy, in the form of rotational energy, and then into electrical energy.
  • Multiple rows, which are termed stages, of turbine blades are used to rotate a turbine shaft.
  • Each steam turbine stage alternately consists of stationary and rotating components: the stationary components are rows of turbine blades mounted to the inside of the casing of the turbine, and are herein referred to as ‘fixed blades’; and the rotating components are rows of turbine blades mounted to a turbine rotor, and are herein referred to as ‘moving blades’.
  • the pressurised steam enters the turbine axially and first impinges on the blade surfaces of a row of fixed blades.
  • the blades deflect the steam onto a row of moving blades which in turn also deflect the steam back to the axial direction, causing themselves move in the opposite direction to the deflected steam.
  • This causes the turbine rotor to rotate and the steam to expand slightly.
  • the next stage of fixed and moving blades repeats the process. This process continues through the turbine until the steam is completely expanded.
  • Each successive stage of blades is optimised to deal with the pressure and volume of the steam expected at the blades' location in the turbine, as the steam will become successively less pressurised as it moves through the successive rows of turbine blades.
  • the fixed turbine blades 103 , 203 can be mounted either directly in the turbine casing 100 , 200 or in separate diaphragms 202 .
  • the blades making up a turbine stage are interconnected to provide damping, thereby avoiding possible vibrations which could damage the turbine.
  • FIG. 1 there are small axial clearances between the fixed blades 103 and the moving blades 105 to prevent the blades contacting each other. There are also small radial clearances between the fixed casing 100 and the rotating components 105 , 108 ; and between the rotor 101 and the stationary components 103 , 109 . These clearances must be made as small as possible to avoid steam leakage, as steam flow through the clearances does not pass through the blading and so is unable to produce any power. Sealing fins 104 are provided in the radial clearances to reduce the amount of steam passing through them. The sealing fins 104 may be fixed either to the rotor 101 , to the casing 100 or to the ends of the blades 103 , 105 .
  • any distortion of the casing 100 due to thermal effects will affect the radial clearance between the ends of the blades 109 and the rotor 101 as the row of blades 103 will no longer form an accurate circle. This can result in some of the ends of the turbine blades 109 contacting the sealing fins 104 , whilst the rotor 101 is rotating, and as a result the sealing fins 104 becoming damaged.
  • the fixed blades can be mounted in a diaphragm as shown in FIG. 2 .
  • the diaphragm 202 , 203 , 204 is usually a welded structure, in two halves to allow it to fit around the turbine shaft, with an outer 202 or inner 204 ring with sufficient mass to ensure that radial distortion is minimised and the blades 203 thus remain in an accurate circle.
  • the outer ring of the diaphragm 202 is mounted to the inner surface of turbine casing 200 in a groove 201 , and the inner ring of the diaphragm 204 fits within a groove 205 in the rotor 207 .
  • the inner ring of the diaphragm 204 does not contact the rotor 207 , creating a clearance in-between, but a finned seal 206 is provided in the groove 205 in the rotor 207 to reduce steam flow through the clearance.
  • the moving blades 209 are positioned axially adjacent to the fixed blades 203 provided in the diaphragm 202 , 203 , 204 and are fixed to the rotor by a moving blade root 208 .
  • a moving blade shroud portion 210 At the end of the moving blades 209 there is provided a moving blade shroud portion 210 , creating a clearance between the moving blade shroud portion 210 and the turbine casing 200 . This clearance is likely to be provided with another finned seal to reduce steam flow through the clearance.
  • FIGS. 3 , 4 and 5 recent designs of diaphragm are much more compact, as shown in FIGS. 3 , 4 and 5 .
  • the fixed blades 303 are mounted in a compact diaphragm 302 , 303 , 309 with an outer ring 302 and an inner ring 309 .
  • Seals 306 B are provided to reduce steam flow through the clearance between the inner ring of the diaphragm 309 and the rotor 301 .
  • the moving blades 304 have blade roots 305 mounted in the rotor 301 .
  • Seals 306 A are provided in the clearance between the outer shroud 307 of the moving blade 304 and the inside surface of an axially projecting portion 310 of the outer ring of the diaphragm 302 .
  • the axially projecting portion 310 of the outer ring of the diaphragm 302 lies radially between the turbine casing 300 and the outer ring of the diaphragm 302 .
  • This design of diaphragm allows for advantageous rotor construction, such as allowing the use of a drum rotor and t-root fixings.
  • the outer and inner rings of the diaphragm 400 must be split at 403 , 407 into two halves, so splitting the diaphragm across its diameter, to allow it to be positioned around a rotor.
  • the differing thermal expansion resulting from the difference in temperatures can cause the two halves of the diaphragm to distort as shown in exaggerated form in FIG. 5 , so that together they form a figure of 8 or oval shape. This means that in some regions of the circumference the stationary parts move closer to the moving parts, closing up the clearance between them which can then cause damage when the fins contact the blades or the rotor, resulting in a permanent increase in leakage as described above.
  • An exemplary purpose of the invention is, therefore, to reduce or eliminate the problem of a compact diaphragm containing a row of turbine blades suffering thermal distortion which results in increased steam leakage and damage to the turbine.
  • the invention provides a turbine diaphragm for an axial flow turbomachine, in which outer shrouds of adjacent fixed blades contact each other circumferentially to form a circumferentially continuous load path, but in which inner shrouds of the blades only contact each other on contact faces oriented to transmit loads in the radial and/or axial directions.
  • This arrangement can avoid circumferential load paths through the inner shrouds and thereby ameliorates the stated problem of thermal distortion.
  • an interference fit can be provided between adjacent inner shrouds on their contact faces, and the interference fit can apply sufficient torque forces to the shrouds to ensure that the contact faces remain in contact with each other throughout the temperature range of operation of the turbomachine.
  • the contact faces for transmitting loads in radial directions contact each other when the diaphragm is in the as-assembled cool condition and throughout all operating conditions of the turbine, but the contact faces for transmitting loads in axial directions only contact each other when the diaphragm reaches an operating temperature.
  • Opposed side edges of the inner shrouds contact corresponding side edges of adjacent inner shrouds of adjacent blades and each opposed side edge comprises a projecting step portion, a recessed step portion and a chamfered step portion that joins the projecting step portion to the recessed step portion, the projecting step portions being at opposite ends of their respective side edges and configured to project into co-operating recessed step portions of adjacent inner shrouds of adjacent blades, the chamfered step portions comprising contact faces operative to transmit loads in axial directions between adjacent inner shroud portions and to prevent circumferential transmission of loads between adjacent inner shroud portions.
  • each opposed side edge of the inner shroud portion further comprises a planar portion
  • the projecting step portions comprise parts of the side edges that jut out relative to the planar portions
  • the recessed step portions comprise parts of the side edges that are undercut relative to the planar portions.
  • exemplary embodiments provides a blade for use in a row of fixed blades in an axial flow turbomachine, comprising:
  • each opposed side edge comprises a projecting step portion, a recessed step portion and a chamfered step portion that joins the projecting step portion to the recessed step portion
  • the projecting step portions being at opposite ends of their respective side edges and configured to project into co-operating recessed step portions of adjacent inner shroud portions of adjacent blades
  • the chamfered step portions being arranged to transfer forces between adjacent inner shroud portions transversely of the circumferential direction in the row of blades and to prevent circumferential transmission of loads between adjacent inner shroud portions.
  • An exemplary turbine blade can interconnect on its inner edge with neighbouring blades, but not transmit circumferential tensile and compressive forces to these neighbouring blades. This can be accomplished by an arrangement that ensures each blade remains free to expand in the circumferential direction whilst keeping contact between the blades. With a small circumferential clearance, for example of less than 0.5 mm, neighbouring blades no longer transmit the tensile or compressive forces that cause the diaphragm to distort under heating or cooling. The blades are held in position through fixing to the outer ring of the diaphragm.
  • FIG. 1 is a partial section taken in a radial plane coincident with the rotational axis of a turbine showing the arrangement of a fixed blade mounted in the casing and a moving blade mounted in the rotor;
  • FIG. 2 is a partial section taken in a radial plane coincident with the rotational axis of a turbine showing the arrangement of a fixed blade mounted in a massive diaphragm and a moving blade mounted in the rotor;
  • FIG. 3 is a partial section taken in a radial plane coincident with the rotational axis of a turbine showing the arrangement of a fixed blade mounted in a compact diaphragm and a moving blade mounted in the rotor;
  • FIG. 4 is an end view along the turbine's rotational axis showing a row of fixed blades mounted in a compact diaphragm seen in isolation from other turbine structure;
  • FIG. 5 is a view similar to FIG. 4 , but showing, in exaggerated form, the row of fixed blades undergoing distortions caused by inner and outer rings of the diaphragm being at different temperatures due to the different thermal inertias of the inner and outer rings;
  • FIG. 6 is a perspective view of three neighbouring turbine blades according to the preferred embodiment of the invention.
  • FIGS. 7 a to 7 c are perspective views of a turbine blade according to the preferred embodiment of the invention, each view being on a different side of the blade;
  • FIG. 8 a is a perspective view of the three neighbouring turbine blades of FIG. 6 being mounted on an outer ring of the diaphragm;
  • FIG. 8 b is a partial section taken on line B-B of FIG. 8 a showing the outer shroud portion of one of the turbine blades contacting the inner surface of the diaphragm's outer ring before welding has occurred;
  • FIGS. 9 a and 9 b are enlarged cross-sectional views of a stepped edge joint on the inner shroud portions of the neighbouring turbine blades of FIG. 6 , showing the joint before undergoing heating ( FIG. 9 a ) and after undergoing heating ( FIG. 9 b );
  • FIG. 10 is a view similar to FIG. 9 b, showing the forces acting on the joint when a full set of turbine blades are inserted into a turbine diaphragm;
  • FIG. 11 is a perspective view of a turbine blade according to an alternative embodiment of the invention.
  • FIGS. 7 a and 7 b show a single turbine blade 700 according to the preferred embodiment of the invention.
  • the blade 700 is formed as a single solid part, forged and machined from a metal block, in three portions: an outer shroud portion 710 , a blade portion 720 and an inner shroud portion 730 .
  • the outer shroud portion 710 is formed as a substantially rectangular or parallelogram-shaped plate having four edge faces 711 , 712 , 714 , 716 . It is curved in the circumferential direction of the turbine diaphragm so that when all the blades are assembled into the diaphragm, adjoining outer shroud portions 710 form a ring whose centre of curvature coincides with the turbine's rotational axis.
  • the radially inner surface 713 of the outer shroud portion 710 forms a flow surface of the turbine passage.
  • the radially outer surface 715 of the outer shroud portion 710 is fixed by welding to an inwardly projecting flange 805 of an outer ring 800 of the diaphragm, as shown in FIGS. 8 a and 8 b and described later.
  • Circumferentially facing edges 712 , 714 of the outer shroud portion 710 extend generally in the axial direction of the turbine and are substantially planar surfaces. When the blades 700 are assembled into the diaphragm, there is circumferential contact between the shroud edges 712 , 714 of neighbouring shrouds to form a circumferentially continuous load path, but as explained below there is no circumferential contact between the inner shroud portions 730 .
  • the axially facing, circumferentially extending edges 711 , 716 of the outer shroud portion 710 are also substantially planar surfaces and the distance between them is the same axial width as the outer ring 800 .
  • the blade portion 720 comprises an aerofoil 721 that connects the outer shroud portion 710 to the inner shroud portion 730 .
  • the inner shroud portion 730 is formed as a substantially rectangular or parallelogram-shaped plate that is curved in the circumferential direction of the turbine diaphragm so that when all the blades are assembled into the diaphragm, adjacent inner shroud portions 730 form a ring whose centre of curvature coincides with the turbine's rotational axis.
  • the radially outer surface 740 of the outer shroud portion 710 forms a flow surface of the turbine passage and the radially inner surface 738 seals against the rotor, e.g., by means of sealing fins mounted on the rotor, similar to fins 306 in FIG. 3 .
  • the inner shroud portion 730 has substantially planar axially facing, circumferentially extending edges 741 , 742 .
  • each circumferentially facing, generally axially extending edge of the inner shroud portion 730 has a projecting step portion 732 , 734 , a complementary recessed step portion 736 , 737 , a chamfered step portion 743 , 744 that joins the projecting step portion to the recessed step portion, and a planar portion 731 , 733 .
  • the planar portions 731 , 733 occupy half the height of their shroud edges, extend the full axial extent of the inner shroud 730 and are located radially outward of the recessed and projecting step portions.
  • the projecting step portions 732 , 734 comprise parts of the shroud edges that jut out relative to the planar portions 731 , 733 of the shroud edges, whereas the recessed step portions 736 , 737 comprise parts of the shroud edges that are undercut relative to the planar portions 731 , 733 .
  • Half the axial extent of the inner shrouds is occupied by the projecting step portions 732 , 734 , which occupy axially opposed positions on the opposed circumferentially facing edges of the inner shroud.
  • the recessed step portions extend over the remaining half of the axial extent of the inner shrouds and occupy axially opposed positions on their respective shroud edges.
  • the sliding differential expansion joints between neighbouring inner shrouds 730 have contact faces comprising the radially outward facing surfaces 735 of the projecting step portions 732 , 734 , the radially inward facing surfaces 735 1 of the recessed step portions 736 , 737 (which may also be characterised as overhanging surfaces of the planar edge portions 731 , 733 ), and the surfaces of chamfered step portions 743 , 744 that form angled faces between the recessed and projecting step portions.
  • the contact faces 735 on any given inner shroud 730 radially abut the contact faces 735 1 on the neighbouring inner shrouds to transmit radial loads between the inner shrouds.
  • the chamfered step portions 743 , 744 on any given inner shroud 730 also abut each other to transmit loads between the inner shrouds transversely of the circumferential direction, i.e., in a generally axial direction.
  • the circumferential facing surfaces 733 , 734 , 736 ; 731 , 732 , 737 of the inner shroud portions 730 do not contact each other, but remain separated by a small gap of about 0.1 mm to 0.5 mm to prevent the transmission of tensile or compressive forces in the circumferential or tangential direction.
  • the design is such that when a full row, or stage, of blades 700 is assembled as a diaphragm, internal twisting forces are produced by flexing the aerofoil portion 721 of the blade during insertion of the blade into the diaphragm. It is arranged that in the as-assembled cool condition, the internal twisting forces cause the abutting contact faces 735 , 735 1 to be forced together. As every abutting contact face has the same amount of internal twisting force acting on it, the net force is zero when all the neighbouring inner shrouds are in mating contact.
  • the inner shroud portion 730 of the blade 700 is adapted to interlock with the neighbouring inner shroud portions without the inner shroud portions coming into contact in the circumferential/tangential direction, i.e., there is no appreciable load transmission between the inner shrouds in directions perpendicular to a plane coincident with the turbine axis.
  • the blades 700 are inserted into a T-shaped outer ring 800 .
  • the radially outer faces 715 of the outer shrouds 710 abut the radially inner face 808 of a radially inwardly projecting flange 805 that forms the stem of the T-shaped outer ring 800 .
  • the abutment of the outer shroud portions 710 and the flange 805 creates two nominally cylindrical channels 804 between the main portion 801 of the outer ring 800 and the interconnected outer shroud portions 710 of the blades 700 .
  • a welding head is inserted into the channels 804 and the outer shrouds are fillet welded to the flange 805 in an automated welding process, as known.
  • the diaphragm is constructed as detailed above, it is cut across its diameter at the outer ring 800 into two semicircular sections.
  • the outer shrouds 710 of the blades 700 are not fixed to each other, so the outer ring 800 is cut at a point where two outer shrouds meet. This allows the two parts of the diaphragm to be placed around the rotor in the turbine when the turbine is being assembled.
  • the two semicircular sections of the outer ring 800 can then be secured together again, e.g., by means of inserting strong bolts through pre-existing bolting flanges of the outer ring 800 , as known, causing the complete circumferential load path in the outer shrouds to be restored.
  • a projecting step portion 734 of the right hand inner shroud 730 projects into a co-operating recessed step portion 737 of the left hand inner shroud, with the radially inward facing contact face 735 1 , formed by the recessed step portion 737 abutting the radially outward facing contact face 735 of the projecting step portion 734 .
  • a projecting step portion 732 ( FIG. 7 c ) of the left hand inner shroud projects into co-operating recessed step portion 736 ( FIG.
  • the expansion joint mechanism between the inner shroud portions 730 a of neighbouring blades 700 a differs from that shown in FIGS. 6 to 10 .
  • the contact faces 735 , 735 1 of the inner shrouds when assembled, contact each other in a radial direction relative to the axis of the turbine, but the chamfered step portions 743 , 744 only contact each other when the turbine reaches an operating temperature.
  • FIG. 11 in the alternative embodiment of FIG.
  • the radial contact faces are omitted and interference contact between the inner shrouds 730 a in the as-assembled cool condition of the diaphragm occurs on the faces of the chamfered step portions 743 1 and 744 1 of the inner shroud edges, leaving a small circumferential gap between the inner shroud edges of adjacent blades, as was the case in the preferred embodiment.
  • This again can avoid transferring forces between inner shrouds 730 a in the circumferential direction because the chamfered step portions 7431 , 744 1 react loads in a generally axial direction.
  • the circumferentially facing edges 731 a, 733 a of the inner shroud portion 730 a are each provided with a projecting step portion 733 a occupying substantially half the axial length of each circumferentially facing edge, the projecting step portions being at axially opposite ends of their respective circumferential facing edges.
  • Each chamfered step portion 743 1 , 744 1 forms an angled face between a recessed step portion 731 a and the projecting step portion 733 a. These angled faces of the chamfered step portions 743 , 744 contact the faces of the chamfered step portions of neighbouring inner shrouds in substantially axially abutting relationship when the turbine diaphragm is assembled.
  • expansion joint mechanism can be used in other types of turbines, such as gas turbines.
  • the invention could also be applicable to fixed blades in compressors.
  • Exemplary embodiments can be used over a wide range of temperatures and pressures experienced by turbines, e.g., 150 to 600 degrees Celsius and 5 to 300 bars. Steel and/or nickel alloys or other appropriate materials can be used in the fabrication of the turbine components described here.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/902,642 2005-03-24 2007-09-24 Diaphragm and blades for turbomachinery Abandoned US20090191053A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GBGB0505978.7A GB0505978D0 (en) 2005-03-24 2005-03-24 Interlocking turbine blades
GB0505978.7 2005-03-24
PCT/EP2006/060937 WO2006100256A1 (fr) 2005-03-24 2006-03-22 Diaphragme et pales pour machines turbo

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2006/060937 Continuation WO2006100256A1 (fr) 2005-03-24 2006-03-22 Diaphragme et pales pour machines turbo

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Publication Number Publication Date
US20090191053A1 true US20090191053A1 (en) 2009-07-30

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US11/902,642 Abandoned US20090191053A1 (en) 2005-03-24 2007-09-24 Diaphragm and blades for turbomachinery

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US (1) US20090191053A1 (fr)
JP (1) JP2008534837A (fr)
CN (1) CN101146980A (fr)
DE (1) DE112006000603T5 (fr)
GB (1) GB0505978D0 (fr)
WO (1) WO2006100256A1 (fr)

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US9127559B2 (en) 2011-05-05 2015-09-08 Alstom Technology Ltd. Diaphragm for turbomachines and method of manufacture
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US8262359B2 (en) 2007-01-12 2012-09-11 Alstom Technology Ltd. Diaphragm for turbomachines and method of manufacture
GB0700633D0 (en) * 2007-01-12 2007-02-21 Alstom Technology Ltd Turbomachine
JP5523109B2 (ja) * 2007-01-12 2014-06-18 アルストム テクノロジー リミテッド ターボ機械のためのダイヤフラム及び製造の方法
US20110200430A1 (en) * 2010-02-16 2011-08-18 General Electric Company Steam turbine nozzle segment having arcuate interface
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US9506362B2 (en) 2013-11-20 2016-11-29 General Electric Company Steam turbine nozzle segment having transitional interface, and nozzle assembly and steam turbine including such nozzle segment
BR112017008795B1 (pt) 2014-11-03 2022-11-08 Nuovo Pignone Tecnologie Srl Setor para a montagem de um estágio de uma turbina e método para fabricar um estágio de uma turbina
CN109048217A (zh) * 2015-09-08 2018-12-21 中国航发常州兰翔机械有限责任公司 航空发动机的燃气涡轮一级导向器
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JP6505860B2 (ja) * 2016-03-15 2019-04-24 東芝エネルギーシステムズ株式会社 タービン及びタービン静翼
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GB0505978D0 (en) 2005-04-27
JP2008534837A (ja) 2008-08-28
WO2006100256A1 (fr) 2006-09-28
CN101146980A (zh) 2008-03-19

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