CN101638994A - Turbomachine component damping structure and method of damping vibration of a turbomachine component - Google Patents

Turbomachine component damping structure and method of damping vibration of a turbomachine component Download PDF

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Publication number
CN101638994A
CN101638994A CN200910159236.9A CN200910159236A CN101638994A CN 101638994 A CN101638994 A CN 101638994A CN 200910159236 A CN200910159236 A CN 200910159236A CN 101638994 A CN101638994 A CN 101638994A
Authority
CN
China
Prior art keywords
damping
damping structure
temperature
turbine components
turbine
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.)
Pending
Application number
CN200910159236.9A
Other languages
Chinese (zh)
Inventor
J·M·德尔乌
J·W·维尔
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 Co
Original Assignee
General Electric Co
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 Co filed Critical General Electric Co
Publication of CN101638994A publication Critical patent/CN101638994A/en
Pending 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D5/10—Anti- vibration means
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • 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

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)

Abstract

The invention relates to a turbomachine compunent damping structure and a method of damping vibration of a turbomachine component. The turbomachine component includes a main body having a surface, anda damping structure mounted to the surface of the main body. The damping structure is formed from a material having a temperature dependent damping characteristic.

Description

The method of the vibration of turbomachine component damping structure and damping turbine components
Technical field
One exemplary embodiment of the present invention relates to turbine technology, and more particularly, relates to the damping structure that is used for turbine components.
Background technique
Turbo machine comprises a plurality of members, and many members wherein are high speed rotating during operation.The operation of turbo machine makes the many members in the turbine components stand to vibrate the stress that is produced.These members comprise compressor structural components, hot gas path (HGP) member, burner section and turbine component.The stress that is produced by vibration can cause fatigue, the tired operation lifetime that can shorten turbine components.
Summary of the invention
According to an one exemplary embodiment of the present invention, a kind of turbine components comprises main body with surface and the damping structure that is installed on the body surfaces.This damping structure is formed by the material with the damping characteristic of deciding with temperature.
According to another one exemplary embodiment of the present invention, the method for a kind of damping turbine components vibration comprises damping structure is installed on the surface of turbine components.This damping structure is formed by the material with the damping characteristic of deciding with temperature.
Description of drawings
Fig. 1 is the example according to the turbine blade that comprises damping structure of one exemplary embodiment of the present invention.
List of parts:
2 turbine components
4 blades
6 base portions
10 main bodys (4)
12 first end section (10)
14 second end section (10)
16 centre/aerofoil profile part sections
18 suction side surfaces
20 is on the pressure side surperficial
30 main body parts (6)
32 first ends (30)
34 the second ends (30)
36 intermediate portions (30)
The 40 first parasitic wings
42 first trench cavities
The 44 second parasitic wings
46 second trench cavities
60 damping structures
Embodiment
Referring to Fig. 1, represented that with 2 it is depicted as the form of turbine blade according to the turbine component of one exemplary embodiment structure of the present invention substantially.Turbine blade 2 is formed by refractory alloy (such as, but not limited to nickel alloy), and comprises aerofoil profile part or blade part 4 and base portion 6.Blade part 4 comprises main body 10, and main body 10 has first end section 12, and this first end section 12 is through centre or aerofoil profile part section 16 and extend to second end section 14.Aerofoil profile part section 16 comprises suction side surface 18 and on the pressure side surperficial 20.Base portion 6 comprises main body part 30, and main body part 30 has first end 32, and this first end 32 extends to the second end 34 through intermediate portion 36.Centre portion 36 comprises the first parasitic wing (angelwing) 40 that defines first trench cavities 42 and the second relative parasitic wing 44 that defines second trench cavities 46.Turbine blade 2 is configured to contiguous a plurality of extra turbine blades and is installed on the rotor disk (not shown) to form turbine.
According to shown in one exemplary embodiment, turbine blade 2 comprises the damping structure 60 of surface on the pressure side on 20 that is fixed to aerofoil profile part section 16.As will becoming obvious more comprehensively hereinafter, damping structure 60 provides the vibration damping characteristic on being applied to aerofoil profile part section 16 time.According to one exemplary embodiment, damping structure 60 is formed by the material with the vibration damping characteristic of deciding with temperature.More specifically, damping structure 60 is included in first damping characteristic of first temperature and in second damping characteristic of second temperature.First damping characteristic is converted to second damping characteristic at damping transition temperature place.In this way, turbine blade 2 is during starts possessing the first damping level and along with operating temperature and speed increase, damping structure 60 is through transition temperatures, so that the vibration damping level of increase to be provided.
According to an aspect of one exemplary embodiment, damping structure 60 is formed by the Stainless Steel Alloy of the damping transition temperature with about 900 (482.2 ℃).Damping structure 60 is fixed on the surface of aerofoil profile part section 16 for example.The damping amount that is provided by damping structure 60 depends on the temperature that vibratory response takes place.This shows, is lower than about 900 °F (482.2 ℃), and then damping is in first level, and is higher than about 900 °F (482.2 ℃), and then damping is in the second higher level.Said system provides 2 to 14 times damping to increase to turbine blade 2.Certainly will be appreciated that above-mentioned scope is an one exemplary embodiment of the present invention.Also can adopt other material with similar or different damping characteristic.The certain material that is adopted depends on desirable damping characteristic under the certain operational parameters/temperature of turbo machine.
In this point, be described to form though should be appreciated that damping structure 60 by stainless steel, also can adopt other alloy with the damping transition temperature in about 800-1400 (426.6 ℃-760 ℃) scopes, comprise glassy alloy.The specific mounting point that should also be clear that damping structure 60 also can be different.That is, as covering substituting of whole aerofoil profile part section, damping structure 60 optionally is applied in the high strain zone, reduces so that obtain maximum stress.In addition, thermal barrier coating 70 can be applied, so that the protection at spallation and oxidation to be provided on the interface between damping structure 60 and the aerofoil profile part section 16.
Depend on material to be joined, damping structure 60 can be applied to desirable turbine components by multiple suitable joining technique.For example, can use welding, soldering or plasma spraying technology that damping structure 60 is applied on the aerofoil profile part section 16.In addition, damping structure 60 can individual layer, multilayer is used, perhaps with damping structure applied in any combination with the damping characteristic that depends on the damping material structural characteristics, such as the co-pending U.S. Patent application No.11/844 that is called " structure that is used for the turbine component damping " (" Structures for Damping of TurbineComponents ") by the name of submitting on August 24th, 2007,462 instruct (this application is combined in herein by reference and integrally).
In general, this written description use-case comes open the present invention, comprises optimal mode, and also makes those skilled in the art can put into practice the present invention, comprises the method for making and using any device or system and carry out any combination.Category of granting patent of the present invention is defined by the claims, and can comprise other example that those skilled in the art expect.If these other examples have the structural element as broad as long with the literal language of claims, if perhaps they comprise the equivalent structure element that does not have substantial differences with the literal language of claims, then these other examples also are intended to be in the category of one exemplary embodiment of the present invention.

Claims (9)

1. a turbine components (2), it comprises:
Main body (10) with surface (18,20); And
Be installed to the damping structure (60) on the surface (18,20) of described main body (10), described damping structure (60) is formed by the material with the damping characteristic of deciding with temperature.
2. turbine components according to claim 1 (2) is characterized in that, described damping structure (60) is included in first damping characteristic of first temperature and in second damping characteristic of second temperature, described second temperature is different from described first temperature.
3. turbine components according to claim 2 (2) is characterized in that, described damping structure (60) comprises the damping transition temperature, and described damping transition temperature is between described first temperature and described second temperature.
4. turbine components according to claim 3 (2) is characterized in that, in the scope of described damping transition temperature between about 800 (426.6 ℃) to about 1400 (760 ℃).
5. turbine components according to claim 4 (2) is characterized in that, described damping transition temperature is about 900 °F (482.2 ℃).
6. turbine components according to claim 1 (2) is characterized in that, described damping structure (60) comprises stainless steel.
7. turbine components according to claim 1 (2) is characterized in that, described turbine components (2) comprises at least one turbine blade (60), and described damping structure is installed on the surface (18,20) of described at least one turbine blade (2).
8. turbine components according to claim 1 (2) is characterized in that, described damping structure (60) is installed on the part on surface (18,20) of described at least one turbine blade (2).
9. turbine components according to claim 1 (2) is characterized in that, described damping structure (60) is installed on the surface (19,20) of described turbine components by a kind of in welding, soldering and the plasma spraying.
CN200910159236.9A 2008-07-30 2009-07-30 Turbomachine component damping structure and method of damping vibration of a turbomachine component Pending CN101638994A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/182,407 US20100028133A1 (en) 2008-07-30 2008-07-30 Turbomachine component damping structure and method of damping vibration of a turbomachine component
US12/182407 2008-07-30

Publications (1)

Publication Number Publication Date
CN101638994A true CN101638994A (en) 2010-02-03

Family

ID=41461833

Family Applications (1)

Application Number Title Priority Date Filing Date
CN200910159236.9A Pending CN101638994A (en) 2008-07-30 2009-07-30 Turbomachine component damping structure and method of damping vibration of a turbomachine component

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US (1) US20100028133A1 (en)
JP (1) JP2010031864A (en)
CN (1) CN101638994A (en)
DE (1) DE102009026279A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105473822A (en) * 2013-08-21 2016-04-06 通用电气公司 Components having vibration dampers enclosed therein and methods of forming such components

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US10577940B2 (en) * 2017-01-31 2020-03-03 General Electric Company Turbomachine rotor blade
US11767765B2 (en) * 2021-09-28 2023-09-26 General Electric Company Glass viscous damper

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JPH0618602U (en) * 1992-08-10 1994-03-11 石川島播磨重工業株式会社 Turbine blade damper
JPH06330704A (en) * 1993-05-26 1994-11-29 Toshiba Corp Coated turbine blade
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105473822A (en) * 2013-08-21 2016-04-06 通用电气公司 Components having vibration dampers enclosed therein and methods of forming such components
US9903434B2 (en) 2013-08-21 2018-02-27 General Electric Company Components having vibration dampers enclosed therein and methods of forming such components

Also Published As

Publication number Publication date
US20100028133A1 (en) 2010-02-04
JP2010031864A (en) 2010-02-12
DE102009026279A1 (en) 2010-02-04

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Application publication date: 20100203