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US20040213672A1 - Undercut leading edge for compressor blades and related method - Google Patents

Undercut leading edge for compressor blades and related method Download PDF

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Publication number
US20040213672A1
US20040213672A1 US10/422,701 US42270103A US2004213672A1 US 20040213672 A1 US20040213672 A1 US 20040213672A1 US 42270103 A US42270103 A US 42270103A US 2004213672 A1 US2004213672 A1 US 2004213672A1
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US
United States
Prior art keywords
leading edge
undercut
blade
airfoil portion
airfoil
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.)
Abandoned
Application number
US10/422,701
Inventor
James Gautreau
Nicholas Martin
Chris Rickert
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
Individual
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 Individual filed Critical Individual
Priority to US10/422,701 priority Critical patent/US20040213672A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: RICKERT, CHRIS A., GAUTREAU, JAMES CHARLES, MARTIN, NICHOLAS FRANCIS
Priority to GB0408867A priority patent/GB2401657A/en
Priority to JP2004127504A priority patent/JP2004324648A/en
Publication of US20040213672A1 publication Critical patent/US20040213672A1/en
Priority to US11/015,746 priority patent/US7121803B2/en
Abandoned 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/433—Polyamides, e.g. NYLON

Definitions

  • This invention relates generally to compressor blades, and specifically, to the provision for an undercut located radially inward of the leading edge of the airfoil portion of the blade.
  • attachment material i.e., material in the root portion of the blade used to secure the blade to the compressor rotor or wheel
  • attachment material directly below, i.e., radially inward of, the airfoil leading edge
  • the void or space created by the material removed may be filled, if necessary, with a discrete acoustic damper of substantially the same shape as the void.
  • the undercut arrangement effectively unloads the leading edge of the airfoil, thereby reducing the local mean and vibratory stresses along the leading edge and thus allows the blade to sustain considerably more damage from water washing and water droplet impact.
  • the undercut is shaped to include a narrow transverse entry slot that opens into a rearward transverse and generally round groove that extends radially inwardly of the base of the slot.
  • the groove is deeper than the slot in a radial direction, giving the appearance of a stylized, sideways “P.”
  • Describing the slot and groove as “transverse” refers to the cross-wise orientation of the slot and groove across the width of the shank portion. Reference to a “radial direction” is with respect to a bucket mounted on the periphery of a turbine rotor wheel.
  • the present invention relates to a compressor blade comprising an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion, the undercut defined by a narrow transverse entry slot opening into a rearward transverse groove.
  • the invention in another aspect, relates to a compressor blade comprising an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof comprising a narrow transverse entry slot opening into a rearward transverse groove to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion; wherein, when assembled on a compressor wheel, a void space created by the undercut is substantially filled by an acoustic damper.
  • the invention relates to a method of unloading a leading edge of an airfoil portion of a compressor blade comprising: a) providing a blade having an airfoil portion with a leading edge, a platform, and an attachment portion adapted to secure the blade to a compressor wheel; and b) removing material from the attachment portion to create an undercut radially inward of the leading edge of the airfoil portion, the undercut defined by a narrow transverse entry slot opening into a rearward transverse groove.
  • FIG. 1 is a perspective view of a compressor blade with an undercut leading edge, and also showing an associated acoustic damper
  • FIG. 2 is an enlarged detail taken from FIG. 1.
  • a compressor blade 10 includes an airfoil portion (or simply, airfoil) 12 , a platform 14 ; and an attachment or root portion 16 that typically is formed with a dovetail configuration that enables the blade to be loaded into a complimentary groove on the compressor wheel or rotor (not shown). Material has been removed from the forward end of the attachment portion 16 , thereby creating an undercut 18 radially inward of the platform 14 (relative to the center of a rotor wheel on which the blade is mounted) and the leading edge 20 of the airfoil 12 .
  • the undercut is shaped to include a narrow transverse entry slot 22 that opens into a rearward transverse groove 24 (FIG.
  • the void space created by the undercut may be filled by an acoustic damper 28 .
  • the damper 28 may be composed of material of the same composition as the blade, or other material such as nylon or other suitable high strength plastics.
  • the damper preferably substantially matches the configuration of the void space created by the undercut 18 .
  • the damper 28 has a relatively thin flange portion 30 that connects to an rearward portion 32 . It will be appreciated that the flange portion 30 will fit within the narrow entry slot 22 and the round rearward portion 32 will fit in the groove 24 .
  • the configuration as described is significant in that the narrow entry slot 22 reduces windage losses while the round groove 24 serves to reduce the stress concentrations adjacent the leading edge 20 of the airfoil portion 12 .
  • the groove 24 may have a diameter of about ⁇ fraction (1/2) ⁇ inch and the slot 22 may have a height of about ⁇ fraction (1/8) ⁇ inch.
  • These dimensions, as well as the length of the slot 22 may vary in accordance with blade size. In any event, the dimensions must be sufficient to offload the leading edge 20 of the airfoil 12 , but must not be so large as to negatively effect the loading of the blade 10 as a whole.
  • the airfoil can sustain considerably more damage from water washing without exceeding the material capability.
  • the erosion process creates small cracks in the leading edge of the airfoil 12 .
  • the blade fails.
  • this edge becomes the life limiting location.
  • Undercutting the blade in accordance with this invention moves the life limiting location to an area approximately 1 inch aft of the leading edge, at the root, on the pressure side of the airfoil. This location is not subjected to the constant water droplet pounding of the waterwash. Consequently, the cracks created by the water washing will no longer propagate and endanger the machine.
  • the leading edge 20 of the airfoil 12 will simply erode with time.

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

Abstract

A compressor blade includes an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion, the undercut defined by a narrow entry slot opening into a rearward transverse groove.

Description

    BACKGROUND OF THE INVENTION
  • This invention relates generally to compressor blades, and specifically, to the provision for an undercut located radially inward of the leading edge of the airfoil portion of the blade. [0001]
  • In large gas turbines used for generating electricity, power companies regularly water wash the machines as soon as any performance degradation is noticed. The water wash is sprayed into the machine at the compressor end, near the hub, and the fluid is flung out into the flow path, cleaning the compressor blades. As a result of this water wash, water droplets impact the first stage blades causing significant erosion along their leading edges, especially at the hub of the airfoil, i.e., where the airfoil meets the platform. This leading edge erosion reduces the high cycle fatigue capability of the material and, in the presence of vibratory excitation, may lead to blade failure. [0002]
  • Accordingly, there is a need to create a more erosion tolerant blade by lowering the mean and vibratory stress levels at the leading edge of the airfoil portion of the blade. [0003]
    • BRIEF DESCRIPTION OF THE INVENTION
  • In accordance with an exemplary embodiment of this invention, attachment material (i.e., material in the root portion of the blade used to secure the blade to the compressor rotor or wheel) directly below, i.e., radially inward of, the airfoil leading edge is removed. This creates an undercut below the hub of the blade, i.e., below the blade platform and the leading edge of the airfoil. The void or space created by the material removed may be filled, if necessary, with a discrete acoustic damper of substantially the same shape as the void. The undercut arrangement effectively unloads the leading edge of the airfoil, thereby reducing the local mean and vibratory stresses along the leading edge and thus allows the blade to sustain considerably more damage from water washing and water droplet impact. [0004]
  • In the exemplary embodiment, the undercut is shaped to include a narrow transverse entry slot that opens into a rearward transverse and generally round groove that extends radially inwardly of the base of the slot. In other words, the groove is deeper than the slot in a radial direction, giving the appearance of a stylized, sideways “P.” Describing the slot and groove as “transverse” refers to the cross-wise orientation of the slot and groove across the width of the shank portion. Reference to a “radial direction” is with respect to a bucket mounted on the periphery of a turbine rotor wheel. [0005]
  • Accordingly, in its broader aspects, the present invention relates to a compressor blade comprising an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion, the undercut defined by a narrow transverse entry slot opening into a rearward transverse groove. [0006]
  • In another aspect, the invention relates to a compressor blade comprising an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof comprising a narrow transverse entry slot opening into a rearward transverse groove to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion; wherein, when assembled on a compressor wheel, a void space created by the undercut is substantially filled by an acoustic damper. [0007]
  • In still another aspect, the invention relates to a method of unloading a leading edge of an airfoil portion of a compressor blade comprising: a) providing a blade having an airfoil portion with a leading edge, a platform, and an attachment portion adapted to secure the blade to a compressor wheel; and b) removing material from the attachment portion to create an undercut radially inward of the leading edge of the airfoil portion, the undercut defined by a narrow transverse entry slot opening into a rearward transverse groove. [0008]
  • The invention will now be described in conjunction with the drawing figures identified below. [0009]
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a perspective view of a compressor blade with an undercut leading edge, and also showing an associated acoustic damper; and [0010]
  • FIG. 2 is an enlarged detail taken from FIG. 1.[0011]
    • DETAILED DESCRIPTION OF THE INVENTION
  • With reference to FIGS. 1 and 2, a [0012] compressor blade 10 includes an airfoil portion (or simply, airfoil) 12, a platform 14; and an attachment or root portion 16 that typically is formed with a dovetail configuration that enables the blade to be loaded into a complimentary groove on the compressor wheel or rotor (not shown). Material has been removed from the forward end of the attachment portion 16, thereby creating an undercut 18 radially inward of the platform 14 (relative to the center of a rotor wheel on which the blade is mounted) and the leading edge 20 of the airfoil 12. The undercut is shaped to include a narrow transverse entry slot 22 that opens into a rearward transverse groove 24 (FIG. 2) that extends radially inwardly of the base 26 of the slot 22. In other words, the groove 24 is deeper than the slot 22, giving the appearance of a stylized, sideways “P.” The void space created by the undercut may be filled by an acoustic damper 28. It will be understood that the damper 28 may be composed of material of the same composition as the blade, or other material such as nylon or other suitable high strength plastics. The damper preferably substantially matches the configuration of the void space created by the undercut 18. Thus, the damper 28 has a relatively thin flange portion 30 that connects to an rearward portion 32. It will be appreciated that the flange portion 30 will fit within the narrow entry slot 22 and the round rearward portion 32 will fit in the groove 24. The configuration as described is significant in that the narrow entry slot 22 reduces windage losses while the round groove 24 serves to reduce the stress concentrations adjacent the leading edge 20 of the airfoil portion 12.
  • In the exemplary embodiment, the [0013] groove 24 may have a diameter of about {fraction (1/2)} inch and the slot 22 may have a height of about {fraction (1/8)} inch. These dimensions, as well as the length of the slot 22 (as measured from the forward edge of the blade to the groove 24) may vary in accordance with blade size. In any event, the dimensions must be sufficient to offload the leading edge 20 of the airfoil 12, but must not be so large as to negatively effect the loading of the blade 10 as a whole.
  • By creating the undercut [0014] 18 to effectively unload the leading edge 20 of the airfoil 12, the airfoil can sustain considerably more damage from water washing without exceeding the material capability. Specifically, the erosion process creates small cracks in the leading edge of the airfoil 12. When the crack length exceeds a propagation threshold value, the blade fails. In a conventional blade with a fully supported leading edge, this edge becomes the life limiting location. Undercutting the blade in accordance with this invention moves the life limiting location to an area approximately 1 inch aft of the leading edge, at the root, on the pressure side of the airfoil. This location is not subjected to the constant water droplet pounding of the waterwash. Consequently, the cracks created by the water washing will no longer propagate and endanger the machine. The leading edge 20 of the airfoil 12 will simply erode with time.
  • With the above arrangement, a more erosion tolerant blade is achieved by lowering the mean and vibratory stress at the leading edge of the blade. [0015]
  • While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims. [0016]

Claims (17)

1. A compressor blade comprising an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion, the undercut defined by a narrow transverse entry slot opening into a rearward transverse groove.
2. The compressor blade of claim 1 wherein, when assembled on a compressor wheel, a void created by the undercut is filled by an acoustic damper having substantially the same shape as the void.
3. The compressor blade of claim 2 wherein said acoustic damper is constructed of a high strength plastic material.
4. The compressor blade of claim 3 wherein said acoustic damper is constructed of nylon.
5. The compressor blade of claim 1 wherein said groove is round and has a diameter of about 0.5 inch.
6. The compressor blade of claim 1 wherein the undercut extends in an axial direction at least to the leading edge of the airfoil portion.
7. A compressor blade comprising an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut in a front face thereof at least and including a transverse, substantially round groove rearward of said front face to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion; wherein, when assembled on a compressor wheel, a void space created by the undercut is substantially filled by an acoustic damper.
8. The compressor blade of claim 7 wherein said acoustic damper is constructed of a high strength plastic material.
9. The compressor blade of claim 7 wherein said acoustic damper is constructed of nylon.
10. The compressor blade of claim 7 wherein a narrow transverse entry slot opens into said transverse groove, said groove having a diameter of about 0.5 inch.
11. A method of unloading a leading edge of an airfoil portion of a compressor blade comprising:
a) providing the blade having the airfoil portion with the leading edge, a platform, and an attachment portion adapted to secure the blade to a compressor wheel; and
b) removing material from the attachment portion to create an undercut radially inward of the leading edge of the airfoil portion, and defined by a narrow transverse entry slot opening into a rearward transverse groove.
12. The method of claim 11 wherein, when assembled on the compressor wheel, a void created by the undercut is filled by an acoustic damper having substantially the same shape as the void.
13. The method of claim 12 wherein said acoustic damper comprises a high strength plastic material.
14. The method of claim 12 wherein said acoustic damper comprises nylon.
15. The method of claim 11 wherein the undercut extends in an axial direction at least to the leading edge of the airfoil portion.
16. The method of claim 11 wherein said rearward transverse groove is substantially round in shape.
17. The method of claim 16 wherein said groove has a diameter of about {fraction (1/2)} inch.
US10/422,701 2002-12-26 2003-04-25 Undercut leading edge for compressor blades and related method Abandoned US20040213672A1 (en)

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Application Number Priority Date Filing Date Title
US10/422,701 US20040213672A1 (en) 2003-04-25 2003-04-25 Undercut leading edge for compressor blades and related method
GB0408867A GB2401657A (en) 2003-04-25 2004-04-21 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
JP2004127504A JP2004324648A (en) 2003-04-25 2004-04-23 Undercut leading edge of compressor blade and method related to it
US11/015,746 US7121803B2 (en) 2002-12-26 2004-12-20 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge

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US10/422,701 US20040213672A1 (en) 2003-04-25 2003-04-25 Undercut leading edge for compressor blades and related method

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US10/327,949 Continuation-In-Part US6902376B2 (en) 2002-12-26 2002-12-26 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge

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US20050135936A1 (en) * 2003-12-17 2005-06-23 Anthony Cherolis Turbine blade with trailing edge platform undercut
US20050254958A1 (en) * 2004-05-14 2005-11-17 Paul Stone Natural frequency tuning of gas turbine engine blades
US20100129228A1 (en) * 2008-11-21 2010-05-27 Alstom Technologies Ltd. Llc Turbine blade platform trailing edge undercut
US20120251331A1 (en) * 2011-04-01 2012-10-04 Alstom Technology Ltd. Turbine Blade Platform Undercut
US10450872B2 (en) 2016-11-08 2019-10-22 Rolls-Royce Corporation Undercut on airfoil coversheet support member
US20230265760A1 (en) * 2022-02-18 2023-08-24 General Electric Company Methods and apparatus to reduce deflection of an airfoil
US12134973B2 (en) * 2023-03-28 2024-11-05 Pratt & Whitney Canada Corp. Test blade for gas turbine engine and method of making
US12331658B2 (en) 2023-03-07 2025-06-17 Pratt & Whitney Canada Corp. Test blade for gas turbine engine and method of making

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GB0427083D0 (en) 2004-12-10 2005-01-12 Rolls Royce Plc Platform mounted components
US20090297351A1 (en) * 2008-05-28 2009-12-03 General Electric Company Compressor rotor blade undercut

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Cited By (13)

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Publication number Priority date Publication date Assignee Title
US20050135936A1 (en) * 2003-12-17 2005-06-23 Anthony Cherolis Turbine blade with trailing edge platform undercut
US6951447B2 (en) * 2003-12-17 2005-10-04 United Technologies Corporation Turbine blade with trailing edge platform undercut
US20050254958A1 (en) * 2004-05-14 2005-11-17 Paul Stone Natural frequency tuning of gas turbine engine blades
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US8287241B2 (en) 2008-11-21 2012-10-16 Alstom Technology Ltd Turbine blade platform trailing edge undercut
US20100129228A1 (en) * 2008-11-21 2010-05-27 Alstom Technologies Ltd. Llc Turbine blade platform trailing edge undercut
US20120251331A1 (en) * 2011-04-01 2012-10-04 Alstom Technology Ltd. Turbine Blade Platform Undercut
US8550783B2 (en) * 2011-04-01 2013-10-08 Alstom Technology Ltd. Turbine blade platform undercut
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