EP1462617B1 - Aubage pour une turbomachine axiale - Google Patents

Aubage pour une turbomachine axiale Download PDF

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Publication number
EP1462617B1
EP1462617B1 EP04101062A EP04101062A EP1462617B1 EP 1462617 B1 EP1462617 B1 EP 1462617B1 EP 04101062 A EP04101062 A EP 04101062A EP 04101062 A EP04101062 A EP 04101062A EP 1462617 B1 EP1462617 B1 EP 1462617B1
Authority
EP
European Patent Office
Prior art keywords
blades
rotor
blade
intermetallic
rotor blades
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
EP04101062A
Other languages
German (de)
English (en)
Other versions
EP1462617A3 (fr
EP1462617A2 (fr
Inventor
Claus Paul Dr. Gerdes
Mohamed Yousef Dr. Nazmy
Hans Dr. Wettstein
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1462617A2 publication Critical patent/EP1462617A2/fr
Publication of EP1462617A3 publication Critical patent/EP1462617A3/fr
Application granted granted Critical
Publication of EP1462617B1 publication Critical patent/EP1462617B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics

Definitions

  • the invention relates to the field of power plant technology. It relates to an axial flow thermal turbomachine according to the preamble of claim 1, which has a reduced rotor weight compared to the known prior art.
  • Thermal turbomachinery As high-pressure compressor for gas turbines or turbines consist essentially of a rotor equipped with blades and a stator, are hung in the vanes. The blades and vanes each have an airfoil and a blade root. To be able to fasten the blades on the rotor or in the stator, grooves are inserted in the stator and on the rotor shaft. In these grooves, the feet of the guide vanes and blades are inserted and locked there.
  • the fixed guide vanes have the task of directing the flow of the compressed or the gaseous medium to be relaxed on the rotating rotor blading so that the energy conversion takes place with the best possible efficiency.
  • blades in one piece from a single material for. B. stainless steel for gas turbine compressor or a nickel-based superalloy for gas turbines to produce and to equip with these similar blades a row of blades.
  • Such blades are hereinafter referred to as conventional blades.
  • the average mass of a row of blades is limited by the carrying capacity of the rotor.
  • a rotor with integral blading in particular for an engine, are circumferentially arranged on the rotor blades, wherein the rotor blade to reduce vibrations, a metallic blade root, a metallic blade leaf portion, at least part of the Blade leading edge and the adjoining portion of the blade surface, and having a blade made of fiber reinforced plastic.
  • the attachment of the blade made of plastic to the metallic blade section by gluing / riveting or by clamping takes place.
  • an impeller for use in a turbomachine which is the promotion of a dirt-laden gas, such as a flue gas known.
  • a dirt-laden gas such as a flue gas known.
  • at least one arranged between the blades enlarged blade is provided on the impeller, the tips of a corrosion-resistant material, such as high-strength steel or titanium, or the total may also consist of such a material.
  • armor and / or armor are provided at the tip of each enlarged blade to maintain a clearance in the dirt deposited near the impeller through which the other blades can pass away from the dirt, thus causing friction problems and associated overhead Energy to operate the turbomachine can be prevented.
  • the aim of the invention is to avoid the mentioned disadvantages of the prior art.
  • the invention is based on the object to develop a thermal turbomachine, which is characterized on the one hand by a reduced total weight of the rotor, and in the other hand, a blade brittle fracture is prevented, so that the life of the machine is increased.
  • this object is achieved in a thermal turbomachine according to the preamble of claim 1, characterized in that at least two uniformly spaced blades are arranged from a ductile material in a row of blades between the intermetallic blades, the blades of the ductile material are either significantly longer than the intermetallic Shovels or the same length have a different blade tip shape than the intermetallic blades, namely blunted blade tips.
  • the advantages of the invention are that the use of the blades of intermetallic compounds on the one hand, the weight of the rotor is reduced, which leads to an increase in the life of the rotor / blade connection and on the other hand, the brittleness of the intermetallic blades no increased risk for the operation of the machine means that the arranged in the same blade row blades made of the ductile material absorb the frictional / Verschieiss publication.
  • intermediate pieces made of a lighter material than the rotor material preferably an intermetallic compound or a titanium alloy, are arranged in the rotor between the rotor blades of a blade row. In this way, the weight of the rotor is additionally reduced.
  • intermetallic blades and the intermediate pieces consist of an intermetallic ⁇ -TiAl compound or an intermetallic orthorhombic TiAl compound, because this inventive use of material leads to a considerable weight reduction of the rotor.
  • the specific gravity of the intermetallic titanium-aluminide compounds is z. B. only about 50% of the density of stainless Cr-Ni-W steel.
  • Fig. 1 shows a cross section through a schematically illustrated blade row of a rotor 1 for a high-pressure compressor of a gas turbine.
  • the rotor 1 is surrounded by a stator 2.
  • the illustrated blade row is equipped with two different types of blades 3, 3 '.
  • the majority of the blades namely the blades 3, are made of an intermetallic compound, preferably a gamma titanium aluminide compound.
  • the blades 3 ' are made of a more ductile material, such as a stainless Cr-Ni steel, as the material for the blades 3.
  • At least two evenly spaced such ductile blades 3 (According to Fig. 1 in the present embodiment, these are four pieces) are arranged in the blade row of the intermetallic blades 3.
  • both blade types 3, 3 'can also have the same length but different shapes of the blade tip 5, as the more ductile blades 3' have blunt blade tips 5.
  • the rotor blades 3 'consist of a stainless steel with the following chemical composition (in% by weight): 0.12 C, ⁇ 0.8 Si, ⁇ 1.0 Mn, 17 Cr, 14.5 Ni, ⁇ 0.5 Mo, 3.3 W, ⁇ 1 Ti, ⁇ 0.045 P, ⁇ 0.03 S, balance Fe.
  • the shaft of the rotor 1 is also made of steel. As is known, the density of steel is about 7.9 g / cm 3 .
  • the intermetallic compound from which the blades 3 are made has the following chemical composition (in% by weight): Ti (30.5-31.5) Al- (8.9-9.5) W- (0.3-0.4) Si.
  • the density of this alloy is advantageously only 4 g / cm 3 , so that the rotor 1 according to the invention is substantially lighter than a rotor with exclusively conventional steel blades.
  • Fig. 2 shows a further embodiment of the invention in a detailed representation.
  • the weight of the rotor 1 can be additionally reduced if - as in Fig. 2 shown - between two adjacent blades of a row of blades of the rotor 1 each intermediate pieces 4 of an intermetallic compound, here of a ⁇ -titanium-aluminide compound, are mounted in the circumferential groove of the rotor 1.
  • the intermetallic compound used for the production of the intermediate pieces 4 has the same chemical composition as the compound used for the blades 3 and described above.
  • Titanium-metal intermetallic compounds with aluminum have some interesting properties that make them attractive as engineering materials in the medium and higher temperature range. This includes their opposite Superiegier Institute and against stainless Steels lower density. However, their technical usability often stands in the way of their brittleness.
  • the above-described ⁇ -titanium-aluminide intermetallic compound is characterized by about 50% lower density than the steel used in this embodiment for the rotor 1 and the blades 3 '. Furthermore, it has an E-modulus at room temperature of 171 GPa and a thermal conductivity ⁇ of 24 W / mK.
  • Table 1 compares the physical properties of the two alloys. Table 1: Physical properties of the different materials Density in g / cm 3 Thermal expansion coefficient in K -1 ⁇ -Ti-Al 4 10x10 -6 Stainless steel 7.9 18.6 x 10 -6
  • the weight reduction of the inventive rotor 1 has an advantageous effect on increasing the life of the machine.
  • the stresses in the blade root fixation in the rotor 1 are reduced.
  • the production of the intermetallic blades 3 and the intermediate pieces 4 is carried out in a known manner by casting, hot-isostatic pressing and heat treatment with a minimum of mechanical post-processing.
  • a further preferred embodiment is shown. It is shown a blade 3, the blade tip 5 is coated.
  • the coating of the blade tip can be done with a hard phase or it can by means of laser welding a wear protection layer be applied. In both cases, the grinding of the blade tips is prevented or reduces the frictional force.
  • an orthorhombic titanium-aluminide alloy having a density of 4.55 g / cm 3 can also be used as the material for the intermetallic blades 3 or the intermediate pieces 4.
  • Orthorhombic titanium aluminide alloys are based on the ordered compound Ti 2 AlNb and have the following chemical composition in (% by weight): Ti (22-27) Al- (21-27) Nb.
  • the intermediate pieces 4 can also be made of a cheaper titanium alloy instead of a gamma titanium-aluminide intermetallic compound, in which case the weight reduction is not quite as strong.
  • the invention is used not only for high-pressure compressor rotors but also for turbine rotors with turbine blades made of known turbine steel, heat-resistant steel or a superalloy, for example a nickel-based superalloy, in which the intermediate pieces between the blades of an intermetallic ⁇ Titanium-aluminide alloy or an intermetallic orthorhombic titanium-aluminide alloy.
  • a superalloy for example a nickel-based superalloy, in which the intermediate pieces between the blades of an intermetallic ⁇ Titanium-aluminide alloy or an intermetallic orthorhombic titanium-aluminide alloy.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Turbomachine thermique traversée axialement et dotée d'un rotor métallique (1) sur lequel des aubes mobiles sont montées dans une rainure périphérique pour former une rangée d'aubes,
    les différentes aubes mobiles d'une rangée d'aubes étant des aubes mobiles (3) en un composé intermétallique,
    caractérisée en ce que
    au moins deux aubes mobiles (3') en un matériau plus ductile sont disposées à distance uniforme les unes des autres entre les aubes mobiles intermétalliques (3) de ladite rangée d'aubes et
    en ce que les aubes mobiles (3') en matériau plus ductile sont nettement plus longues que les aubes intermétalliques (3) ou, pour une même longueur, présentent une pointe (5) d'aube émoussée d'une autre forme que les aubes intermétalliques (3).
  2. Turbomachine selon la revendication 1, caractérisée en ce que des pièces intermédiaires (4) en un matériau plus léger que le matériau du rotor (1), de préférence en un composé intermétallique ou en un alliage de titane, sont de plus disposées entre des aubes mobiles (3, 3') voisines d'une rangée d'aubes.
  3. Turbomachine selon les revendications 1 ou 2, caractérisée en ce que le composé intermétallique est un alliage de γ-titane-aluminure ou un alliage orthorhombique de titane et d'aluminure.
  4. Turbomachine selon la revendication 3, caractérisée en ce que l'alliage de γ-titane-aluminure présente la composition chimique suivante (en % en poids) : Ti-(30,5-31,5)Al-(8,9-9,5)W-(0,3-0,4)Si.
  5. Turbomachine selon l'une des revendications 1 à 4, caractérisée en ce que les pointes (5) des aubes mobiles (3) sont revêtues d'une phase dure.
  6. Turbomachine selon la revendication 5, caractérisée en ce qu'une couche de protection contre l'usure est appliquée par soudage au laser sur la pointe des aubes.
  7. Turbomachine selon l'une des revendications 1 à 6, caractérisée en ce que la turbomachine est un compresseur à haute pression d'une turbine à gaz, dotée d'un rotor (1) constitué d'acier inoxydable au Cr-Ni.
  8. Turbomachine selon l'une des revendications 1 à 7, caractérisée en ce que les aubes mobiles (3') plus ductiles que les aubes mobiles intermétalliques (3) sont constituées d'un acier inoxydable au Cr-Ni, d'un acier réfractaire pour aubes de turbine ou d'un superalliage.
EP04101062A 2003-03-26 2004-03-16 Aubage pour une turbomachine axiale Expired - Lifetime EP1462617B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10313489 2003-03-26
DE10313489A DE10313489A1 (de) 2003-03-26 2003-03-26 Axial durchströmte thermische Turbomaschine

Publications (3)

Publication Number Publication Date
EP1462617A2 EP1462617A2 (fr) 2004-09-29
EP1462617A3 EP1462617A3 (fr) 2006-11-15
EP1462617B1 true EP1462617B1 (fr) 2012-09-19

Family

ID=32798100

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04101062A Expired - Lifetime EP1462617B1 (fr) 2003-03-26 2004-03-16 Aubage pour une turbomachine axiale

Country Status (4)

Country Link
US (1) US7048507B2 (fr)
EP (1) EP1462617B1 (fr)
JP (1) JP4638681B2 (fr)
DE (1) DE10313489A1 (fr)

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EP1902160B1 (fr) * 2005-07-12 2009-03-18 Alstom Technology Ltd Couche calorifuge ceramique
US7811053B2 (en) * 2005-07-22 2010-10-12 United Technologies Corporation Fan rotor design for coincidence avoidance
EP1953344B1 (fr) * 2007-02-05 2012-04-11 Siemens Aktiengesellschaft Aube de turbine
US8100641B2 (en) * 2008-09-09 2012-01-24 General Electric Company Steam turbine having stage with buckets of different materials
DE102009030398A1 (de) * 2009-06-25 2010-12-30 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren einer Schaufel für eine Strömungsmaschine
ES2583756T3 (es) * 2011-04-01 2016-09-22 MTU Aero Engines AG Disposición de álabes para una turbomáquina
US20130078084A1 (en) * 2011-09-23 2013-03-28 United Technologies Corporation Airfoil air seal assembly
US10309232B2 (en) * 2012-02-29 2019-06-04 United Technologies Corporation Gas turbine engine with stage dependent material selection for blades and disk
US9429023B2 (en) * 2013-01-14 2016-08-30 Honeywell International Inc. Gas turbine engine components and methods for their manufacture using additive manufacturing techniques
US20150093237A1 (en) * 2013-09-30 2015-04-02 General Electric Company Ceramic matrix composite component, turbine system and fabrication process
FR3018849B1 (fr) * 2014-03-24 2018-03-16 Safran Aircraft Engines Piece de revolution pour un rotor de turbomachine
WO2016167214A1 (fr) * 2015-04-17 2016-10-20 三菱日立パワーシステムズ株式会社 Pale de rotor de turbine à vapeur et procédé permettant de fabriquer une pale de rotor de turbine à vapeur
DE102017221641A1 (de) * 2017-12-01 2019-06-06 MTU Aero Engines AG Schaufelkranz mit mischbeschaufelung
US11299993B2 (en) 2019-10-28 2022-04-12 Honeywell International Inc. Rotor assembly for in-machine grinding of shroud member and methods of using the same

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Also Published As

Publication number Publication date
US20060073019A1 (en) 2006-04-06
EP1462617A3 (fr) 2006-11-15
JP4638681B2 (ja) 2011-02-23
US7048507B2 (en) 2006-05-23
EP1462617A2 (fr) 2004-09-29
JP2004293550A (ja) 2004-10-21
DE10313489A1 (de) 2004-10-14

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