WO2000071855A1 - Device for controlling air flow in a turbine blade - Google Patents

Device for controlling air flow in a turbine blade Download PDF

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Publication number
WO2000071855A1
WO2000071855A1 PCT/CA2000/000572 CA0000572W WO0071855A1 WO 2000071855 A1 WO2000071855 A1 WO 2000071855A1 CA 0000572 W CA0000572 W CA 0000572W WO 0071855 A1 WO0071855 A1 WO 0071855A1
Authority
WO
WIPO (PCT)
Prior art keywords
flowpath
turbine blade
cooling air
inlet opening
flow
Prior art date
Application number
PCT/CA2000/000572
Other languages
French (fr)
Inventor
Andre Chevrefils
Daniel G. Grigore
Original Assignee
Pratt & Whitney Canada Corp.
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 Pratt & Whitney Canada Corp. filed Critical Pratt & Whitney Canada Corp.
Priority to DE60023884T priority Critical patent/DE60023884T2/en
Priority to JP2000620217A priority patent/JP2003500586A/en
Priority to EP00929179A priority patent/EP1185764B1/en
Priority to CA002373192A priority patent/CA2373192C/en
Publication of WO2000071855A1 publication Critical patent/WO2000071855A1/en

Links

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped

Definitions

  • the present invention relates to gas turbines, and more particularly to a device for controlling the flow of cooling air through a flowpath in a turbine blade.
  • gases are compressed in a compressor section, burned with fuel in a combustion section and expanded in a turbine section to extract work from the hot, pressurized gases.
  • the rotor assembly of the turbine section includes a disk having a plurality of circumferentially disposed, spaced apart blade attachment slots, each of which is provided with a turbine blade having a root radially disposed therein and spaced from the bottom part of the slot, thus leaving a cavity therebetween .
  • the hot gases impart energy to the rotor assembly.
  • the material of the blades can tolerate a maximum temperature beyond which its vulnerability to damage increases, leading to a lower service life.
  • cooling air It is known to cool turbine blades by flowing cooling air extracted from the compressor section.
  • the cooling air is flowed to the cavities formed in the rotor disk through a stator assembly supporting the combustion section and the rotor assembly. From each cavity, the cooling air is flowed through one or more flowpaths in the blade internal core from an inlet opening at the root thereof and exiting through openings provided near the trailing edge of the blade.
  • U.S. Patent No. 4,626,169 issued to Hsing et al . describes a perforated rectangular cast seal plate, which is disposed in the cavity between the slot and the blade root, against the bottom surface thereof, and which comprises baffles to accomodate a rivet to retain the blade.
  • the seal plate is provided with a coating applied thereon by a flame spraying method and is installed by tapping it with a hammer in the cavity, the coating providing a tight fit between the seal plate and the disk walls defining the cavity.
  • a problem with such a device is that the casting of the seal plate needs to correspond to the exact dimensions of the cavity and cooperate with the rivet thereof, which requires expensive machining operations. The openings in the plate can also get clogged.
  • One aim of the present invention is to provide an inexpensive device that can be easily inserted in the inlet opening of a blade flowpath and retained therein.
  • a device for controlling a flow of cooling air through a flowpath in a turbine blade for cooling the turbine blade comprises a plug member for reducing the flow of cooling air through the flowpath.
  • the plug member comprises a blocking portion adapted to be inserted in the flowpath, and a retaining portion joined to the blocking portion for retaining the plug member at an inlet opening of the flowpath, the retaining portion being adapted to engage against walls of the blade forming the flowpath thereof.
  • the retaining portion may comprise a first flange and a second flange joined to the first flange with the blocking portion.
  • the blocking portion may comprise a first intermediate panel, a second intermediate panel and a bight portion joining the first and second intermediate panels, the first and second intermediate panels joining the first and second flanges, respectively.
  • the plug member may be made of a spring metal material .
  • a turbine blade assembly comprising a turbine blade with a root portion defining an inlet opening, and an inner wall defining a flowpath extending from the inlet opening to an outlet opening, provided at an airfoil surface of the turbine blade, for a flow of cooling air, and a device for controlling the flow of cooling air through the flowpath, the device comprising a blocking portion inserted in the inlet opening, and a retaining portion urging against the root portion defining the inlet opening.
  • a method for adjusting a flow of cooling air through a flowpath in a turbine blade for cooling the turbine blade comprises a) providing a plug member comprising a blocking portion and a retaining portion, and b) inserting the blocking portion in an inlet opening of the flowpath.
  • a method for adjusting a flow of cooling air through a flowpath having a cross-sectional area in a turbine blade for cooling the turbine blade comprises a) determining a flow of cooling air required through the flowpath, b) cutting a plug member comprising a blocking portion and a retaining portion to a width to reduce the cross-sectional area of the flowpath to the required flow of cooling air, and c) inserting the blocking portion in an inlet opening of the flowpath.
  • Fig. 1 is a perspective view illustrating an embodiment of a plug in accordance with the present invention in operative position in the blade;
  • Fig. 2 is a perspective view of the plug shown in
  • Fig. 3 is a fragmentary radial cross-sectional view of a portion of a rotor assembly according to the embodiment illustrated in Fig. 1.
  • a turbine blade 10 having an airfoil section 12 and a root section 14 opposite the airfoil section 12.
  • the root section 14 includes a fir tree shaped attachment section 16 ended by a root bottom surface 18.
  • the root bottom surface 18 is provided with an inlet opening 20 at the center thereof.
  • An inner wall 22 of the turbine blade 10 defines a flowpath 24, which extends from the inlet opening 20 through the turbine blade 10 to outlets provided at the surface of the tip and/or the side trailing edge of the airfoil section.
  • the turbine blade 10 is shown with an embodiment of a device for controlling a flow of cooling air in a turbine blade, herein shown in the form of a plug 26, inserted in the inlet opening 20 of the flowpath 24 to reduce the cross-sectional area of the inlet opening 20.
  • the plug 26 is made of a strip of a resilient material such as a spring metal, which is symmetrically formed relative to a plane through axis A bisecting the strip, and which is bent into a first flange 28, first and second elongated intermediate panels 30 and 32 and a second flange 34.
  • the strip of the present embodiment has a thickness of 0.008-0.011 inches.
  • the blocking portion 36 includes a bight portion 38, which connects the first and second intermediate panels 30 and 32.
  • the bight portion 38 has a diameter 2R, in the present embodiment 0.045 inches, which corresponds essentially to the width of the flowpath 24 of the turbine blade 10, in which the plug 26 is to be inserted, as will be described hereinafter.
  • the first and second intermediate panels 30 and 32 are substantially planar and slightly outwardly-flared relative to the plane, such that the distance between the ends thereof opposite the bight portion 38 corresponds to twice the diameter 2R of the bight portion 38.
  • the distance between the ends of the intermediate panels 30 and 32 opposite the bight portion 38 is 0.09 inches in the present embodiment.
  • the height of the blocking portion 36, measured from the bight portion 38 to the ends of the intermediate panels 30 and 32, is 0.2 inches. However, the height of the blocking portion 36 can vary.
  • the first and second intermediate panels 30 and 32 axe respectively curved into the first and second flanges 28 and 34, each of which is outwardly-directed relative to the axis A and disposed at a right angle relative to the intermediate panels 30 and 32.
  • the flanges 28 and 34 are slightly acutely angled relative to a second plane through an axis B normal to the axis A when the plug 26 is in an inoperative position, as shown in Fig. 2.
  • the flanges define a retaining portion 39.
  • Each flange 28 and 34 has a 0.07 inch length in the present embodiment. However, the length of the flanges 28 and 34 can vary.
  • first and second flanges 28 and 34 are adapted to urge against the root bottom surface 18 of the turbine blade 10 on either side of the inlet opening 20 of the flowpath 24 and to retain the plug 26 in place.
  • the rotor assembly includes a rotor disk 40, which is mounted on an engine shaft and is rotatable relative to the shaft axial axis (not shown) .
  • the rotor disk 40 has an outer rim 42 having a plurality of circumferentially disposed, spaced apart, axially extending slots 44 corresponding to the fir tree shaped attachment section 16 of the turbine blade 10.
  • the blade attachment section 16 when in a corresponding blade attachment slot 44, leaves a cavity 46 between the outer rim 42 and the root bottom surface 18.
  • the plug 26 is mounted to the turbine blade 10 by inserting the bight portion 38 through the inlet opening 20 provided at the root surface 18 of the turbine blade 10 and into the flowpath 24, until the flanges 28 and 34 against the root bottom surface 18 of the turbine blade 10.
  • the first and second intermediate panels 30 and 32 are biased against the inner wall 22 defining the flowpath 24.
  • the plug 26 is maintained in position by the friction of the intermediate panels 30 and 32 with the inner wall 22.
  • the rotation of the rotor disk 40 creates a centrifugal force which maintains the flanges 28 and 34 against the root surface 18 of the turbine blade 10. Sealing of the flowpath 24 is provided by the shape of the plug 26 and by the CF load.
  • the plug 26 is tailored to reduce the cross- sectional area of the flowpath 24 to allow a required airflow to circulate.
  • the width of the strip is cut to a width that reduces the cross-sectional area of the flowpath 24 to the required flow of cooling air, allowing an effective airflow between the inner wall 22 of the turbine blade 10 and one or both sides of the plug 26, when the plug 26 is in an operative position in the turbine blade 10.
  • a flow of cooling air was reduced from 0.66% to 0.4% of the engine core flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to gas turbines and more particularly to a device for controlling the flow of cooling air through a flowpath in a turbine blade (10). The device can be inserted in the inlet opening (20) of the blade flowpath (24) and be retained therein. The device comprises a plug member (26) for adjusting the flow of cooling air through the flowpath (24). The plug member (26) comprises a retaining portion for retaining the plug member at the inlet opening (20) of the flowpath (24) and a blocking portion inserted within the flowpath for reducing the cross-sectional area of the inlet opening (20). Such a device is inexpensive and can be easily inserted in the inlet opening of a blade flowpath and retained therein.

Description

DEVICE FOR CONTROLLING AIR FLOW IN A TURBINE BLADE
BACKGROUND OF THE INVENTION
(a) Field of the Invention The present invention relates to gas turbines, and more particularly to a device for controlling the flow of cooling air through a flowpath in a turbine blade.
(b) Description of Prior Art
In a turbine engine, gases are compressed in a compressor section, burned with fuel in a combustion section and expanded in a turbine section to extract work from the hot, pressurized gases. The rotor assembly of the turbine section includes a disk having a plurality of circumferentially disposed, spaced apart blade attachment slots, each of which is provided with a turbine blade having a root radially disposed therein and spaced from the bottom part of the slot, thus leaving a cavity therebetween .
During operation of the engine, the hot gases impart energy to the rotor assembly. However, the material of the blades can tolerate a maximum temperature beyond which its vulnerability to damage increases, leading to a lower service life.
It is known to cool turbine blades by flowing cooling air extracted from the compressor section. The cooling air is flowed to the cavities formed in the rotor disk through a stator assembly supporting the combustion section and the rotor assembly. From each cavity, the cooling air is flowed through one or more flowpaths in the blade internal core from an inlet opening at the root thereof and exiting through openings provided near the trailing edge of the blade.
A problem which arises with such a configuration is that the amount of cooling air flowing through the blades cannot be adjusted for the amount of cooling air required. Devices for adjusting the flow of cooling air into turbine blades are known. For example, U.S. Patent No. 4,626,169 issued to Hsing et al . describes a perforated rectangular cast seal plate, which is disposed in the cavity between the slot and the blade root, against the bottom surface thereof, and which comprises baffles to accomodate a rivet to retain the blade. The seal plate is provided with a coating applied thereon by a flame spraying method and is installed by tapping it with a hammer in the cavity, the coating providing a tight fit between the seal plate and the disk walls defining the cavity.
A problem with such a device is that the casting of the seal plate needs to correspond to the exact dimensions of the cavity and cooperate with the rivet thereof, which requires expensive machining operations. The openings in the plate can also get clogged.
It would be highly desirable to be provided with an inexpensive device that could be easily inserted in the inlet opening of the blade flowpath and be retained therein .
SUMMARY OF THE INVENTION
One aim of the present invention is to provide an inexpensive device that can be easily inserted in the inlet opening of a blade flowpath and retained therein.
In accordance with the present invention there is provided a device for controlling a flow of cooling air through a flowpath in a turbine blade for cooling the turbine blade. The device comprises a plug member for reducing the flow of cooling air through the flowpath. The plug member comprises a blocking portion adapted to be inserted in the flowpath, and a retaining portion joined to the blocking portion for retaining the plug member at an inlet opening of the flowpath, the retaining portion being adapted to engage against walls of the blade forming the flowpath thereof.
The retaining portion may comprise a first flange and a second flange joined to the first flange with the blocking portion.
The blocking portion may comprise a first intermediate panel, a second intermediate panel and a bight portion joining the first and second intermediate panels, the first and second intermediate panels joining the first and second flanges, respectively.
The plug member may be made of a spring metal material .
In accordance with the present invention there is also provided a turbine blade assembly comprising a turbine blade with a root portion defining an inlet opening, and an inner wall defining a flowpath extending from the inlet opening to an outlet opening, provided at an airfoil surface of the turbine blade, for a flow of cooling air, and a device for controlling the flow of cooling air through the flowpath, the device comprising a blocking portion inserted in the inlet opening, and a retaining portion urging against the root portion defining the inlet opening.
In accordance with the present invention, there is further provided a method for adjusting a flow of cooling air through a flowpath in a turbine blade for cooling the turbine blade. The method comprises a) providing a plug member comprising a blocking portion and a retaining portion, and b) inserting the blocking portion in an inlet opening of the flowpath.
In accordance with the present invention, there is further provided a method for adjusting a flow of cooling air through a flowpath having a cross-sectional area in a turbine blade for cooling the turbine blade. The method comprises a) determining a flow of cooling air required through the flowpath, b) cutting a plug member comprising a blocking portion and a retaining portion to a width to reduce the cross-sectional area of the flowpath to the required flow of cooling air, and c) inserting the blocking portion in an inlet opening of the flowpath.
BRIEF DESCRIPTION OF THE DRAWINGS
Having thus generally described the nature of the invention, reference will now be made to the accompanying drawings, showing by way of illustration a preferred embodiment thereof, in which like numerals refer to like components, and in which:
Fig. 1 is a perspective view illustrating an embodiment of a plug in accordance with the present invention in operative position in the blade; Fig. 2 is a perspective view of the plug shown in
Fig . 1 ; and
Fig. 3 is a fragmentary radial cross-sectional view of a portion of a rotor assembly according to the embodiment illustrated in Fig. 1.
DETAILED DESCRIPTION OF THE INVENTION
As may be seen in Fig. 1, there is shown a turbine blade 10 having an airfoil section 12 and a root section 14 opposite the airfoil section 12. The root section 14 includes a fir tree shaped attachment section 16 ended by a root bottom surface 18. The root bottom surface 18 is provided with an inlet opening 20 at the center thereof. An inner wall 22 of the turbine blade 10 defines a flowpath 24, which extends from the inlet opening 20 through the turbine blade 10 to outlets provided at the surface of the tip and/or the side trailing edge of the airfoil section. The turbine blade 10 is shown with an embodiment of a device for controlling a flow of cooling air in a turbine blade, herein shown in the form of a plug 26, inserted in the inlet opening 20 of the flowpath 24 to reduce the cross-sectional area of the inlet opening 20.
Referring now to Fig. 2, the plug 26 is made of a strip of a resilient material such as a spring metal, which is symmetrically formed relative to a plane through axis A bisecting the strip, and which is bent into a first flange 28, first and second elongated intermediate panels 30 and 32 and a second flange 34. The strip of the present embodiment has a thickness of 0.008-0.011 inches. The first and second intermediate panels 30 and 32, disposed adjacent one another and at the center of the sheet, define a blocking portion 36.
The blocking portion 36 includes a bight portion 38, which connects the first and second intermediate panels 30 and 32. The bight portion 38 has a diameter 2R, in the present embodiment 0.045 inches, which corresponds essentially to the width of the flowpath 24 of the turbine blade 10, in which the plug 26 is to be inserted, as will be described hereinafter. The first and second intermediate panels 30 and 32 are substantially planar and slightly outwardly-flared relative to the plane, such that the distance between the ends thereof opposite the bight portion 38 corresponds to twice the diameter 2R of the bight portion 38. The distance between the ends of the intermediate panels 30 and 32 opposite the bight portion 38 is 0.09 inches in the present embodiment. The height of the blocking portion 36, measured from the bight portion 38 to the ends of the intermediate panels 30 and 32, is 0.2 inches. However, the height of the blocking portion 36 can vary.
The first and second intermediate panels 30 and 32 axe respectively curved into the first and second flanges 28 and 34, each of which is outwardly-directed relative to the axis A and disposed at a right angle relative to the intermediate panels 30 and 32. In this manner, the flanges 28 and 34 are slightly acutely angled relative to a second plane through an axis B normal to the axis A when the plug 26 is in an inoperative position, as shown in Fig. 2. The flanges define a retaining portion 39. Each flange 28 and 34 has a 0.07 inch length in the present embodiment. However, the length of the flanges 28 and 34 can vary.
In operation, the first and second flanges 28 and 34 are adapted to urge against the root bottom surface 18 of the turbine blade 10 on either side of the inlet opening 20 of the flowpath 24 and to retain the plug 26 in place.
Referring now to Fig. 3, the rotor assembly includes a rotor disk 40, which is mounted on an engine shaft and is rotatable relative to the shaft axial axis (not shown) . The rotor disk 40 has an outer rim 42 having a plurality of circumferentially disposed, spaced apart, axially extending slots 44 corresponding to the fir tree shaped attachment section 16 of the turbine blade 10. The blade attachment section 16, when in a corresponding blade attachment slot 44, leaves a cavity 46 between the outer rim 42 and the root bottom surface 18.
In operation, the plug 26 is mounted to the turbine blade 10 by inserting the bight portion 38 through the inlet opening 20 provided at the root surface 18 of the turbine blade 10 and into the flowpath 24, until the flanges 28 and 34 against the root bottom surface 18 of the turbine blade 10. During the insertion of the plug 26 into the flowpath 24, the first and second intermediate panels 30 and 32 are biased against the inner wall 22 defining the flowpath 24.
The plug 26 is maintained in position by the friction of the intermediate panels 30 and 32 with the inner wall 22. When the rotor assembly is in motion, the rotation of the rotor disk 40 creates a centrifugal force which maintains the flanges 28 and 34 against the root surface 18 of the turbine blade 10. Sealing of the flowpath 24 is provided by the shape of the plug 26 and by the CF load.
The plug 26 is tailored to reduce the cross- sectional area of the flowpath 24 to allow a required airflow to circulate. The width of the strip is cut to a width that reduces the cross-sectional area of the flowpath 24 to the required flow of cooling air, allowing an effective airflow between the inner wall 22 of the turbine blade 10 and one or both sides of the plug 26, when the plug 26 is in an operative position in the turbine blade 10.
In one example, a flow of cooling air was reduced from 0.66% to 0.4% of the engine core flow.
While the invention has been described with particular reference to the illustrated embodiment, it will be understood that numerous modifications thereto will appear to those skilled in the art. Accordingly, the above description and accompanying drawings should be taken as illustrative of the invention and not in a limiting sense.

Claims

WHAT IS CLAIMED IS;
1. A device for controlling a flow of cooling air through a flowpath in a turbine blade for cooling said turbine blade, said device comprising a plug member for reducing said flow of cooling air through said flowpath, said plug member comprising: a) a blocking portion adapted to be inserted in said flowpath; and b) a retaining portion joined to said blocking portion for retaining said plug member at an inlet opening of said flowpath, said retaining portion being adapted to engage against a wall of said turbine blade defining said flowpath.
2. A device according to claim 1, wherein said retaining portion comprises a first flange and a second flange joined to said first flange with said blocking portion.
3. A device according to claim 2, wherein said blocking portion comprises a first intermediate panel, a second intermediate panel and a bight portion joining said first and second intermediate panels, said first and second intermediate panels joining said first and second flanges, respectively.
4. A device according to claim 3, wherein said plug member is made of a spring metal material.
5. A turbine blade assembly comprising a turbine blade with a root portion defining an inlet opening, and an inner wall defining a flowpath extending from said inlet opening to an outlet opening, provided at an airfoil surface of said turbine blade, for a flow of cooling air, and a device for controlling said flow of cooling air through said flowpath, said device comprising a blocking portion inserted in said inlet opening, and a retaining portion urging against said root portion defining said inlet opening.
6. A method for adjusting a flow of cooling air through a flowpath in a turbine blade for cooling said turbine blade, said method comprising: a) providing a plug member comprising a blocking portion and a retaining portion; and b) inserting said blocking portion in an inlet opening of said flowpath.
7. A method for adjusting a flow of cooling air through a flowpath having a cross-sectional area in a turbine blade for cooling said turbine blade, said method comprising: a) determining a flow of cooling air required through said flowpath; b) cutting a plug member comprising a blocking portion and a retaining portion to a width to reduce said cross-sectional area of said flowpath to said required flow of cooling air; and c) inserting said blocking portion in an inlet opening of said flowpath.
PCT/CA2000/000572 1999-05-19 2000-05-18 Device for controlling air flow in a turbine blade WO2000071855A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE60023884T DE60023884T2 (en) 1999-05-19 2000-05-18 DEVICE FOR REGULATING THE AIR FLOW IN A TURBINE BLADE
JP2000620217A JP2003500586A (en) 1999-05-19 2000-05-18 Control device for airflow in turbine blades
EP00929179A EP1185764B1 (en) 1999-05-19 2000-05-18 Device for controlling air flow in a turbine blade
CA002373192A CA2373192C (en) 1999-05-19 2000-05-18 Device for controlling air flow in a turbine blade

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/314,292 1999-05-19
US09/314,292 US6176677B1 (en) 1999-05-19 1999-05-19 Device for controlling air flow in a turbine blade

Publications (1)

Publication Number Publication Date
WO2000071855A1 true WO2000071855A1 (en) 2000-11-30

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Country Status (6)

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US (1) US6176677B1 (en)
EP (1) EP1185764B1 (en)
JP (1) JP2003500586A (en)
CA (1) CA2373192C (en)
DE (1) DE60023884T2 (en)
WO (1) WO2000071855A1 (en)

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US20100034662A1 (en) * 2006-12-26 2010-02-11 General Electric Company Cooled airfoil and method for making an airfoil having reduced trail edge slot flow
US8016547B2 (en) * 2008-01-22 2011-09-13 United Technologies Corporation Radial inner diameter metering plate
US8221083B2 (en) * 2008-04-15 2012-07-17 United Technologies Corporation Asymmetrical rotor blade fir-tree attachment
US8348614B2 (en) * 2008-07-14 2013-01-08 United Technologies Corporation Coolable airfoil trailing edge passage
US8113784B2 (en) * 2009-03-20 2012-02-14 Hamilton Sundstrand Corporation Coolable airfoil attachment section
JP5495893B2 (en) * 2010-03-30 2014-05-21 三菱重工業株式会社 Gas turbine and method for modifying the same
US8562286B2 (en) 2010-04-06 2013-10-22 United Technologies Corporation Dead ended bulbed rib geometry for a gas turbine engine
US20120315139A1 (en) * 2011-06-10 2012-12-13 General Electric Company Cooling flow control members for turbomachine buckets and method
JP6613611B2 (en) 2015-05-15 2019-12-04 株式会社Ｉｈｉ Turbine blade mounting structure
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1065344A3 (en) * 1999-06-30 2003-12-03 General Electric Company Turbine blade trailing edge cooling openings and slots
GB2485477A (en) * 2010-11-10 2012-05-16 Rolls Royce Corp Gas turbine blade attachment opening plug
US8888455B2 (en) 2010-11-10 2014-11-18 Rolls-Royce Corporation Gas turbine engine and blade for gas turbine engine
GB2485477B (en) * 2010-11-10 2017-04-26 Rolls Royce Corp Gas turbine engine and blade for gas turbine engine

Also Published As

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US6176677B1 (en) 2001-01-23
DE60023884T2 (en) 2006-07-20
CA2373192A1 (en) 2000-11-30
EP1185764B1 (en) 2005-11-09
CA2373192C (en) 2008-02-12
DE60023884D1 (en) 2005-12-15
JP2003500586A (en) 2003-01-07
EP1185764A1 (en) 2002-03-13

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