EP1462614B1 - Turbine thermique à écoulement axial - Google Patents

Turbine thermique à écoulement axial Download PDF

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Publication number
EP1462614B1
EP1462614B1 EP04101054.7A EP04101054A EP1462614B1 EP 1462614 B1 EP1462614 B1 EP 1462614B1 EP 04101054 A EP04101054 A EP 04101054A EP 1462614 B1 EP1462614 B1 EP 1462614B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
blades
density
turbomachine
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
EP04101054.7A
Other languages
German (de)
English (en)
Other versions
EP1462614A2 (fr
EP1462614A3 (fr
Inventor
Claus Paul Gerdes
Mohamed Yousef Nazmy
Hans 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 EP1462614A2 publication Critical patent/EP1462614A2/fr
Publication of EP1462614A3 publication Critical patent/EP1462614A3/fr
Application granted granted Critical
Publication of EP1462614B1 publication Critical patent/EP1462614B1/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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures

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.
  • Out DE 14 26 816 A1 is an axial turbomachine with a compressor blade ring in which Verguss sapll GmbHe of casting resin or aluminum or Al alloys are arranged between adjacent blades known. By casting the spaces between the blade roots, the circumferential distance should be kept exactly as well as materials and production times saved.
  • 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, in which due to a reduced weight, the life of the rotor is increased.
  • this object is achieved in a thermal turbomachine according to the preamble of claim 1, characterized in that the intermediate pieces between the blades of a blade row consist of intermetallic compounds.
  • the advantages of the invention are that on the one hand, the weight of the rotor is reduced, and on the other hand, the brittleness of the intermetallic spacers no increased risk for the operation of the machine means.
  • 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 titanium-aluminide intermetallic compounds is only about 50% of that of stainless Cr-Ni-W steel.
  • FIGURE shows a cross section through the rotor according to the invention of a high-pressure compressor for a gas turbine.
  • Fig. 1 shows a cross section through a blade row of a rotor 1 for a high-pressure compressor of a gas turbine.
  • the rotor 1 is surrounded by a stator 2.
  • blades 3, 3 ' are mounted, while in the stator 2 vanes 5 are mounted.
  • the blades 3, 3 ', 5 are exposed to a temperature of approximately 600 ° C. for several thousand hours at a pressure of approximately 32 bar.
  • the shaft of the rotor 1 is also made of steel.
  • the density of steel is about 7.9 g / cm 3 .
  • intermediate pieces 4 are respectively mounted in the circumferential groove of the rotor 1 in a blade row of the rotor 1.
  • these intermediate pieces 4 are made of an intermetallic compound, here of a ⁇ -titanium-aluminide compound.
  • This intermetallic compound used for the production of the intermediate pieces 4 has the following chemical composition (in% by weight): Ti (30.5-31.5) Al- (8.9-9.5) W- (0.3-0.4) Si.
  • Titanium-metal intermetallic compounds with aluminum have some interesting properties that make them attractive as engineering materials in the medium and higher temperature range. These include their lower compared to superalloys and lower than stainless steels. However, their technical usability often stands in the way of their brittleness.
  • the ⁇ -titanium-aluminide intermetallic compound described above is characterized by about 50% lower density than the steel used in this embodiment for the rotor and the blades. Furthermore, it has an E-modulus at room temperature of 171 GPa and a thermal conductivity ⁇ of 24 W / mK.
  • Table 1 compares further 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 has an advantageous effect on increasing the life of the machine.
  • intermetallic spacers is carried out in a known manner by casting, hot-isostatic pressing and heat treatment with a minimum of mechanical post-processing.
  • the intermediate piece 4 of the high-pressure compressor may, for example, also be made of a known intermetallic orthorhombic titanium-aluminide alloy with a density of 4.55 g / cm 3 .
  • Orthorhombic titanium aluminide alloys are based on the ordered compound Ti 2 AlNb and have the following chemical composition: Ti (22-27) Al- (21-27) Nb.
  • Ti (22-27) Al- (21-27) Nb The inventive use of a titanium high-temperature alloy, which has, for example, the following chemical composition (in% by weight): 0.06 C, 0.4 Si, 5.8 Al, 4 Sn, 4 Zr, 0.5 Mo, ⁇ 0.05 Fe, 0.11 O, ⁇ 0.03 N, ⁇ 0.006 H, remainder Ti, is conceivable.
  • the invention not only for high-pressure compressor rotors, but also for turbine rotors with turbine blades made of a superalloy, for example a nickel-based superalloy, in which the intermediate pieces between the blades, for example of a ⁇ -titanium-aluminide intermetallic alloy or an intermetallic orthorhombic titanium-aluminide alloy.
  • a superalloy for example a nickel-based superalloy
  • the intermediate pieces between the blades for example of a ⁇ -titanium-aluminide intermetallic alloy or an intermetallic orthorhombic titanium-aluminide alloy.

Landscapes

  • 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 (4)

  1. Turbomachine thermique à écoulement axial comprenant un rotor (1) en matériau métallique ayant une première densité (D1), des aubes mobiles (3, 3') et des pièces intermédiaires (4) étant montées en alternance dans une rainure périphérique, lesdites pièces intermédiaires (4) se composant d'un matériau ayant une deuxième densité (D2) inférieure à la première densité (D1), caractérisée en ce que le matériau de deuxième densité (D2) est un composé intermétallique.
  2. Turbomachine selon la revendication 1, caractérisée en ce que le composé intermétallique est un alliage de γ-titane-aluminiure ou un alliage orthorhombique de titane/aluminiure.
  3. Turbomachine selon la revendication 2, caractérisée en ce que l'alliage de γ-titane-aluminiure présente la composition chimique suivante (indications en pourcentages en poids) : Ti-(30,5-31,5)Al-(8,9-9,5)W-(0,3-0,4)Si.
  4. Turbomachine selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la turbomachine est un compresseur haute pression d'une turbine à gaz avec un rotor (1) qui se compose essentiellement d'un acier inoxydable Cr-Ni.
EP04101054.7A 2003-03-26 2004-03-15 Turbine thermique à écoulement axial Expired - Lifetime EP1462614B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10313490 2003-03-26
DE10313490A DE10313490A1 (de) 2003-03-26 2003-03-26 Axial durchströmte thermische Turbomaschine

Publications (3)

Publication Number Publication Date
EP1462614A2 EP1462614A2 (fr) 2004-09-29
EP1462614A3 EP1462614A3 (fr) 2006-11-15
EP1462614B1 true EP1462614B1 (fr) 2015-01-28

Family

ID=32798101

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04101054.7A Expired - Lifetime EP1462614B1 (fr) 2003-03-26 2004-03-15 Turbine thermique à écoulement axial

Country Status (4)

Country Link
US (1) US7037079B2 (fr)
EP (1) EP1462614B1 (fr)
JP (1) JP2004293549A (fr)
DE (1) DE10313490A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE502006003197D1 (de) * 2005-07-12 2009-04-30 Alstom Technology Ltd Keramische wärmedämmschicht
DE102009030398A1 (de) * 2009-06-25 2010-12-30 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren einer Schaufel für eine Strömungsmaschine
WO2014093826A2 (fr) 2012-12-14 2014-06-19 United Technologies Corporation Coulage à multiples injections
SG11201503276PA (en) 2012-12-14 2015-06-29 United Technologies Corp Hybrid turbine blade for improved engine performance or architecture

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE513407C (de) 1926-11-02 1930-11-27 Conservenfabrik Und Trocknungs Verfahren zum Trocknen von Fruchtsaeften
US2327839A (en) * 1940-03-26 1943-08-24 Bbc Brown Boveri & Cie Turbine construction
GB750397A (en) * 1951-12-10 1956-06-13 Power Jets Res & Dev Ltd Damped turbine and dynamic compressor blades
US2857134A (en) * 1954-03-17 1958-10-21 Parsons C A & Co Ltd Assembly of blades for turbines and the like
DE1426816A1 (de) * 1963-07-02 1969-03-13 Licentia Gmbh Verfahren zur Herstellung eines Schaufelkranzes einer Axialstroemungsmaschine,insbesondere eines Axialverdichters
JPS57168005A (en) * 1981-04-10 1982-10-16 Hitachi Ltd Rotor structue for axial machines
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
DE3789776T2 (de) * 1986-02-05 1994-08-18 Hitachi Ltd Hitzebeständiger Stahl und daraus hergestellte Gasturbinenteile.
EP0513407B1 (fr) * 1991-05-13 1995-07-19 Asea Brown Boveri Ag Procédé de fabrication d' une aube de turbine
US5906096A (en) * 1992-08-06 1999-05-25 Hitachi, Ltd. Compressor for turbine and gas turbine
GB9606963D0 (en) * 1996-04-02 1996-06-05 Rolls Royce Plc A root attachment for a turbomachine blade
DE19751129C1 (de) 1997-11-19 1999-06-17 Mtu Muenchen Gmbh FAN-Rotorschaufel für ein Triebwerk
DE10110102C2 (de) 2000-12-18 2002-12-05 Deutsch Zentr Luft & Raumfahrt Rotorschaufel

Also Published As

Publication number Publication date
US7037079B2 (en) 2006-05-02
JP2004293549A (ja) 2004-10-21
DE10313490A1 (de) 2004-10-14
US20060062674A1 (en) 2006-03-23
EP1462614A2 (fr) 2004-09-29
EP1462614A3 (fr) 2006-11-15

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