EP2770166B1 - Dämpfer für Kompressorschaufelfüsse - Google Patents
Dämpfer für Kompressorschaufelfüsse Download PDFInfo
- 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
- Authority
- 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
Links
- 239000000463 material Substances 0.000 claims description 19
- 238000005452 bending Methods 0.000 claims description 13
- 229910001235 nimonic Inorganic materials 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 14
- 230000005489 elastic deformation Effects 0.000 description 4
- 230000002441 reversible effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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
- 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)
- Zwischenteil (1), das in einer Umfangsnut (4) einer Trommel (6), in die Schaufeln (2) eingeführt werden, positioniert ist, wobei das Zwischenteil (1) zwischen zwei benachbarten Verdichterschaufeln (2, 20) in einem Hochdruck-Axialverdichter positioniert ist und in seiner Ruheposition ein gewisses Maß an Vorbiegung (A) zeigt, das durch die Elastizitätseigenschaften des Materials, aus dem das angeführte Zwischenteil (1) hergestellt ist, bereitgestellt wird, wobei das Maß an Vorbiegung (A) in der Umfangsrichtung (200) bezüglich der Trommel (6) vorliegt,
dadurch gekennzeichnet, dass es in der diametralen Richtung (300) bezüglich der Trommel (6) weiter vorgebogen wird, wodurch dieses Zwischenteil (1) in einer im Wesentlichen sphärischen Form konfiguriert ist. - Zwischenteil (1) nach Anspruch 1, dadurch gekennzeichnet, dass es in zwei im Wesentlichen senkrechte Richtungen vorgebogen wird.
- Zwischenteil (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass es aus einem Material mit Hochelastizitätseigenschaften bei hoher Temperatur und mit einer Härte, die unter der des Materials, aus dem die Trommel (6) konfiguriert ist, liegt, hergestellt ist.
- Zwischenteil (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass es aus Nimonic 90®-Material hergestellt ist.
- Gasturbine (100) mit einem Hochdruck-Axialverdichter, wobei ein Zwischenteil (1) nach einem der Ansprüche 1-4 zwischen jeweils zwei benachbarten Verdichterschaufeln (2, 20) positioniert ist.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13156035.1A EP2770166B1 (de) | 2013-02-20 | 2013-02-20 | Dämpfer für Kompressorschaufelfüsse |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13156035.1A EP2770166B1 (de) | 2013-02-20 | 2013-02-20 | Dämpfer für Kompressorschaufelfüsse |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2770166A1 EP2770166A1 (de) | 2014-08-27 |
EP2770166B1 true EP2770166B1 (de) | 2017-04-12 |
Family
ID=47722178
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13156035.1A Active EP2770166B1 (de) | 2013-02-20 | 2013-02-20 | Dämpfer für Kompressorschaufelfüsse |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2770166B1 (de) |
Families Citing this family (1)
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)
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 |
-
2013
- 2013-02-20 EP EP13156035.1A patent/EP2770166B1/de active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP2770166A1 (de) | 2014-08-27 |
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