EP2770166A1 - Damper for compressor blade feet - Google Patents
Damper for compressor blade feet Download PDFInfo
- Publication number
- EP2770166A1 EP2770166A1 EP13156035.1A EP13156035A EP2770166A1 EP 2770166 A1 EP2770166 A1 EP 2770166A1 EP 13156035 A EP13156035 A EP 13156035A EP 2770166 A1 EP2770166 A1 EP 2770166A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- intermediate part
- compressor
- blades
- drum
- high pressure
- 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.)
- Granted
Links
- 239000000463 material Substances 0.000 claims abstract description 21
- 238000005452 bending Methods 0.000 claims abstract description 14
- 229910001235 nimonic Inorganic materials 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 13
- 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
- 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.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- 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.
- In a gas turbine engine, 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.
- The type of high pressure compressors widely used for heavy gas turbines (see
Figure 1 ) are axial compressors, in which the working fluid principally flows parallel to the axis of rotation: a shaft drives a central drum having a plurality of circumferential grooves, where a plurality of blades are inserted, the blades rotating around the shaft. 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. - Different devices and solutions exist in the state of the art between adjacent compressor blades of a row in a compressor used in gas turbines. For example, it is known in the state of the art, as per document
US 2010/0135782 A1 , a compressor having a plurality of blades arranged in a circumferential direction, comprising ring segments held by a seal holder with respect to a shaft, such that a seal member is provided on an inner peripheral side of the seal holder to ensure sealability with the shaft. However, during start-up of the compressor, when typically the highest stresses occur, undesired stress can happen between adjacent blades that can potentially damage the compressor structure. - Document
GB 687,507 - Also known in the art are intermediate parts used in the circumferential grooves of a compressor row, between adjacent compressor blades. Typically, 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. As a result, 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.
- Therefore, 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 inserted in a circumferential groove in a high pressure axial compressor, between two adjacent compressor blades in a row, typically in a high pressure axial compressor used in a gas turbine. The intermediate part of the invention has certain degree of pre-bending in the circumferential direction, at a rest position, provided by the elastic properties of the material making up 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.
- Compared to the prior art, 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.
- Besides, 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 foregoing objects and many of the attendant advantages of this invention will become more readily appreciated as the same becomes better understood by reference to the following detailed description when taken in conjunction with the accompanying drawings, wherein.
-
Figure 1 shows a heavy gas turbine engine, comprising a high pressure axial compressor, known in the prior art. -
Figure 2 shows an intermediate part inserted in a circumferential groove in a high pressure axial compressor as the one shown inFigure 1 , between two adjacent compressor blades in a row, according to the present invention. -
Figure 3 shows in section an intermediate part having certain degree of pre-bending according to the present invention, used between adjacent compressor blades in a high pressure axial compressor, as the one shown inFigure 1 . -
Figures 4a and 4b show details of an intermediate part without any pre-bending, used between adjacent blades in a high pressure axial compressor, according to the known prior art.Figures 4c and 4d show details of an intermediate part having certain degree of pre-bending according to the present invention, used between adjacent compressor blades in a high pressure axial compressor. -
Figures 5a and 5b show details of an intermediate part having certain degree of spherical pre-bending according to a first embodiment of the present invention. -
Figures 6a and 6b show details of an intermediate part having certain degree of pre-bending in two opposite directions, according to a second embodiment of the present invention. - The present invention discloses an
intermediate part 1 located in acircumferential groove 4 between twoadjacent compressor blades heavy gas turbine 100, as the one shown inFigure 1 . In theheavy gas turbine 100, a shaft 5 drives acentral drum 6 having a plurality ofcircumferential grooves 4, where a plurality ofblades 2 are inserted, theblades 2 rotating around the shaft 5. Theintermediate part 1 presents in its rest position (shown inFigure 3 ) certain degree of pre-bending A in thecircumferential direction 200, thanks to the elastic properties of the material making up the intermediate part 1.The material making up theintermediate part 1 must avoid any plastic deformation of saidintermediate part 1. The thickness and width of theintermediate part 1 will depend on the properties of the material configuring it. - When start-up of the compressor occurs, the
drum 6 is still cold but theintermediate part 1 and theadjacent blades intermediate part 1 being deformed. The deformation of thisintermediate part 1 is effected by the elastic deformation of the material configuring saidintermediate part 1, without any plastic deformation. - According to an embodiment of the invention, the
intermediate part 1 is made of Nimonic 90 ® material, which is a material having an elastic behaviour similar to a spring. However, other types of materials can also be used for theintermediate parts 1, selected upon the temperature and pressure of the axial compressor. - According to a first embodiment of the invention, the
intermediate part 1 is spherically pre-bended, in thecircumferential direction 200 and also in thediametric direction 300, with respect to thedrum 6, as shown inFigures 5a and 5b . According to a second embodiment of the invention, theintermediate part 1 is pre-bended in two opposite directions, typically in two substantially perpendicular directions:Figures 6a and 6b show an embodiment where theintermediate part 1 is pre-bended in thecircumferential direction 200 and also following adirection 400 that is substantially perpendicular to thecircumferential direction 200. - Any other shape of the
intermediate part 1 making it to be pre-bended in such a way that theintermediate part 1 acts like a spring in thecircumferential direction 200 with respect to thedrum 6 is possible. - Besides, the elastic bending of the pre-bended
intermediate part 1 of the invention during start-up allows avoiding any plastic deformation in theintermediate part 1, which leads to keeping in the circumferential gap betweenadjacent compressor blades intermediate piece 1 from escaping during start-up of the compressor. - 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. - Although the present invention has been fully described in connection with preferred embodiments, it is evident that modifications may be introduced within the scope thereof, not considering this as limited by these embodiments, but by the contents of the following claims.
-
- 1
- Intermediate part
- 2
- Compressor blade
- 20
- Adjacent compressor blade
- A
- Pre-bending value of the intermediate part in the circumferential direction
- 4
- Circumferential groove in the drum
- 100
- Heavy Gas Turbine
- 200
- Circumferential direction in the drum
- 5
- Shaft in the heavy gas turbine
- 6
- Central drum in the compressor
- 300
- Diametric direction in the drum
- 400
- Direction substantially perpendicular to the circumferential direction of the drum
Claims (7)
- Intermediate part (1) located in a circumferential groove (4) of a drum (6) where blades (2) are inserted, the intermediate part (1) being located between two adjacent compressor blades (2, 20) in a high pressure axial compressor and being characterized in that it presents in its rest position certain degree of pre-bending (A) provided by the elastic properties of the material of which the cited intermediate part (1) is made.
- Intermediate part (1) according to claim 1, characterized in that the degree of pre-bending (A) is in the circumferential direction (200) with respect to the drum (6).
- Intermediate part (1) according to claim 2, characterized in that it is further pre-bended in the diametric direction (300) with respect to the drum (6), thus being configured this intermediate part (1) in a substantially spherical shape.
- Intermediate part (1) according to claim 1, characterized in that it is pre-bended in two substantially perpendicular directions.
- Intermediate part (1) according to any of the previous claims, characterized in that it is made of a material having high elastic properties at high temperature, and with hardness less than that of the material configuring the drum (6).
- Intermediate part (1) according to any of the previous claims, characterized in that it is made of Nimonic 90 ® material.
- Gas turbine (100) with a high pressure axial compressor, such that an intermediate part (1) according to any of claims 1-6 is located between each two adjacent compressor blades (2, 20).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13156035.1A EP2770166B1 (en) | 2013-02-20 | 2013-02-20 | Damper for compressor blade feet |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13156035.1A EP2770166B1 (en) | 2013-02-20 | 2013-02-20 | Damper for compressor blade feet |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2770166A1 true EP2770166A1 (en) | 2014-08-27 |
EP2770166B1 EP2770166B1 (en) | 2017-04-12 |
Family
ID=47722178
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13156035.1A Active EP2770166B1 (en) | 2013-02-20 | 2013-02-20 | Damper for compressor blade feet |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2770166B1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2019056326A (en) * | 2017-09-21 | 2019-04-11 | 三菱日立パワーシステムズ株式会社 | Turbine blade group and rotary machine comprising the same |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE554119C (en) * | 1932-07-13 | Alfred Buechi Dipl Ing | Resilient blade attachment for gas and steam turbines | |
GB687507A (en) | 1949-06-28 | 1953-02-18 | Cem Comp Electro Mec | Improvements in turbine and compressor blades |
GB2169664A (en) * | 1984-12-20 | 1986-07-16 | Gen Electric | Blade root seal |
US20100135782A1 (en) | 2007-10-15 | 2010-06-03 | Ikuo Nakamura | Assembling method of stator blade ring segment, stator blade ring segment, coupling member, welding method |
-
2013
- 2013-02-20 EP EP13156035.1A patent/EP2770166B1/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE554119C (en) * | 1932-07-13 | Alfred Buechi Dipl Ing | Resilient blade attachment for gas and steam turbines | |
GB687507A (en) | 1949-06-28 | 1953-02-18 | Cem Comp Electro Mec | Improvements in turbine and compressor blades |
GB2169664A (en) * | 1984-12-20 | 1986-07-16 | Gen Electric | Blade root seal |
US20100135782A1 (en) | 2007-10-15 | 2010-06-03 | Ikuo Nakamura | Assembling method of stator blade ring segment, stator blade ring segment, coupling member, welding method |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2019056326A (en) * | 2017-09-21 | 2019-04-11 | 三菱日立パワーシステムズ株式会社 | Turbine blade group and rotary machine comprising the same |
Also Published As
Publication number | Publication date |
---|---|
EP2770166B1 (en) | 2017-04-12 |
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