EP2770166B1 - Amortisseur pour pieds d'aubes de compresseur - Google Patents

Amortisseur pour pieds d'aubes de compresseur Download PDF

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Publication number
EP2770166B1
EP2770166B1 EP13156035.1A EP13156035A EP2770166B1 EP 2770166 B1 EP2770166 B1 EP 2770166B1 EP 13156035 A EP13156035 A EP 13156035A EP 2770166 B1 EP2770166 B1 EP 2770166B1
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EP
European Patent Office
Prior art keywords
intermediate part
compressor
blades
drum
adjacent
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.)
Active
Application number
EP13156035.1A
Other languages
German (de)
English (en)
Other versions
EP2770166A1 (fr
Inventor
Alexandre Arkhipov
Vladimir Karaban
Igor Putchkov
Wilhelm Ebeling
Charles Raymond Matz
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
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General Electric Technology GmbH
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 Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP13156035.1A priority Critical patent/EP2770166B1/fr
Publication of EP2770166A1 publication Critical patent/EP2770166A1/fr
Application granted granted Critical
Publication of EP2770166B1 publication Critical patent/EP2770166B1/fr
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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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2300/501—Elasticity

Definitions

  • the present invention relates to an intermediate part inserted in a circumferential groove between adjacent compressor blades in a high pressure axial compressor, in particular to an intermediate part used between adjacent blades of a row in a high pressure axial compressor used in gas turbines.
  • a single turbine section is made up of a disc or hub that holds many turbine blades. That turbine section is connected to a compressor section via a shaft. In the compressor, air is compressed, raising its pressure and temperature, the high temperature and high pressure exhaust gases passing then through the turbine stages. The turbine stages extract energy from this flow, lowering the pressure and temperature of the air.
  • Axial flow compressors produce a continuous flow of high temperature compressed gas, having high efficiencies and large mass flow capacity, particularly in relation to their cross-section. They do, however, require several rows of blades to achieve large pressure rises making them complex and expensive.
  • Document GB 687,507 discloses a distance piece being located in the space between the intermediate portions of two adjacent compressor blades: this distance piece is made such that it follows the shape of the intermediate gap where it is located, either being able to swing about a bolt (two pairs of knuckles are located in its lower side) or are secured rigidly. In any case, no deformation is possible with this distance pieces so they are subjected to very high stresses that can damage the pieces and the compressor blades, also being this solution both complex and expensive.
  • Document GB2169664 discloses an elastomeric seal with pre-bending sections for preventing air leakage between platforms and between blade roots of the compressor of a gas turbine engine.
  • intermediate parts used in the circumferential grooves of a compressor row, between adjacent compressor blades.
  • these intermediate parts are made of a material with limited elastic properties such that plastic deformation occurs during start-up, a critical condition in which strong lateral compressive forces act on the intermediate parts.
  • these intermediate parts which are made from a softer material than the compressor blades, deform plastically to a significant degree, allowing the formation of large circumferential gaps between adjacent blades causing that some of the intermediate pieces are not retained in place, leading to extensive damage to the compressor blades, resulting in a forced outage of the gas turbine.
  • Plastic deformation as it is not reversible, should be avoided in a too big extent; elastic deformation instead, as it is reversible, should be targeted for.
  • an intermediate part that avoids plastic deformation would avoid large circumferential gaps, thus avoiding the escape of the intermediate-part, also avoiding undesired turbine forced outage.
  • the present invention is oriented towards these needs.
  • the present invention relates to an intermediate part according to claim 1, and a gas turbine according to claim 5.
  • the intermediate part When start-up of the high pressure axial compressor occurs, the intermediate part is forced to deform tangentially, in the circumferential direction, with respect to its pre-bending shape in order to absorb the compressive forces resulting from the reduced space between the adjacent compressor blades: with the design of the invention, when start-up takes place, the deformation of this intermediate part is effected by the elastic deformation of the whole intermediate part material acting as an elastic element, typically acting as a spring, without any plastic deformation in the intermediate part.
  • the pre-bending of the intermediate part of the invention requires a lower thickness of this intermediate part, allowing at the same time that the distance between adjacent blades is maintained at any given operational condition, steady (base load) or transient (start-up), and also while the compressor is not in operation.
  • this elastic deformation of the pre-bended intermediate part material of the invention during start-up avoids any plastic deformation in the intermediate part material, thus avoiding any plasticity (surface imprint) in the joined adjacent compressor blades, such that the dimensions of the circumferential gap between adjacent blades remains unchanged, and thus the intermediate part is prevented from escaping.
  • the present invention discloses an intermediate part 1 located in a circumferential groove 4 between two adjacent compressor blades 2 and 20, typically in a compressor row in a high pressure axial compressor used in a heavy gas turbine 100, as the one shown in Figure 1 .
  • a shaft 5 drives a central drum 6 having a plurality of circumferential grooves 4, where a plurality of blades 2 are inserted, the blades 2 rotating around the shaft 5.
  • the intermediate part 1 presents in its rest position (shown in Figure 3 ) certain degree of pre-bending A in the circumferential direction 200, thanks to the elastic properties of the material making up the intermediate part 1.
  • the material making up the intermediate part 1 must avoid any plastic deformation of said intermediate part 1.
  • the thickness and width of the intermediate part 1 will depend on the properties of the material configuring it.
  • the intermediate part 1 is made of Nimonic 90 ® material, which is a material having an elastic behaviour similar to a spring.
  • Nimonic 90 ® material which is a material having an elastic behaviour similar to a spring.
  • other types of materials can also be used for the intermediate parts 1, selected upon the temperature and pressure of the axial compressor.
  • the intermediate part 1 is spherically pre-bended, in the circumferential direction 200 and also in the diametric direction 300, with respect to the drum 6, as shown in Figures 5a and 5b .
  • the intermediate part 1 is pre-bended in two opposite directions, typically in two substantially perpendicular directions:
  • Figures 6a and 6b show an embodiment where the intermediate part 1 is pre-bended in the circumferential direction 200 and also following a direction 400 that is substantially perpendicular to the circumferential direction 200.
  • any other shape of the intermediate part 1 making it to be pre-bended in such a way that the intermediate part 1 acts like a spring in the circumferential direction 200 with respect to the drum 6 is possible.
  • the elastic bending of the pre-bended intermediate part 1 of the invention during start-up allows avoiding any plastic deformation in the intermediate part 1, which leads to keeping in the circumferential gap between adjacent compressor blades 2 and 20, thus preventing the intermediate piece 1 from escaping during start-up of the compressor.
  • the intermediate part 1 Different materials can be used for the intermediate part 1: the main requirement for the material choice is its good elastic properties at high temperatures; in principle, elastic - ideal plastic behavior should be targeted for. Besides, its hardness should be less than that of the material configuring the drum 6 in the compressor.

Landscapes

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

Claims (5)

  1. Partie intermédiaire (1) située dans une rainure circonférentielle (4) d'un rotor (6) où sont insérées des aubes (2), la partie intermédiaire (1) étant située entre deux aubes de compresseur (2, 20) adjacentes dans un compresseur axial haute pression et présentant, dans sa position de repos, un certain degré de préflexion (A) produit par les propriétés élastiques du matériau dont la partie intermédiaire (1) est constituée, le degré de préflexion (A) étant dans la direction circonférentielle (200) par rapport au rotor (6), caractérisée en ce qu'elle est en outre préfléchie dans la direction diamétrale (300) par rapport au rotor (6), ladite partie intermédiaire (1) étant ainsi configurée de façon à présenter une forme essentiellement sphérique.
  2. Partie intermédiaire (1) selon la revendication 1, caractérisée en ce qu'elle est préfléchie dans deux directions essentiellement perpendiculaires.
  3. Partie intermédiaire (1) selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle est constituée d'un matériau présentant des propriétés de haute élasticité à haute température, et présentant une dureté inférieure à celle du matériau dont est constitué le rotor (6).
  4. Partie intermédiaire (1) selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle est constituée du matériau Nimonic 90®.
  5. Turbine à gaz (100) comportant un compresseur axial haute pression, tel qu'une partie intermédiaire (1) selon l'une quelconque des revendications 1 à 4 est située entre chaque paire d'aubes de compresseur (2, 20) adjacentes.
EP13156035.1A 2013-02-20 2013-02-20 Amortisseur pour pieds d'aubes de compresseur Active EP2770166B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13156035.1A EP2770166B1 (fr) 2013-02-20 2013-02-20 Amortisseur pour pieds d'aubes de compresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13156035.1A EP2770166B1 (fr) 2013-02-20 2013-02-20 Amortisseur pour pieds d'aubes de compresseur

Publications (2)

Publication Number Publication Date
EP2770166A1 EP2770166A1 (fr) 2014-08-27
EP2770166B1 true EP2770166B1 (fr) 2017-04-12

Family

ID=47722178

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13156035.1A Active EP2770166B1 (fr) 2013-02-20 2013-02-20 Amortisseur pour pieds d'aubes de compresseur

Country Status (1)

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EP (1) EP2770166B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2019056326A (ja) * 2017-09-21 2019-04-11 三菱日立パワーシステムズ株式会社 タービン翼群及びこのタービン翼群を備える回転機械

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE554119C (de) * 1932-07-13 Alfred Buechi Dipl Ing Nachgiebige Schaufelbefestigung fuer Gas- und Dampfturbinen
GB687507A (en) 1949-06-28 1953-02-18 Cem Comp Electro Mec Improvements in turbine and compressor blades
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
JP5091615B2 (ja) 2007-10-15 2012-12-05 三菱重工業株式会社 静翼環セグメントの組立方法、静翼環セグメント、結合部材、溶接方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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