US3574482A - Turbomachinery blades - Google Patents

Turbomachinery blades Download PDF

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US3574482A
US3574482A US793434*A US3574482DA US3574482A US 3574482 A US3574482 A US 3574482A US 3574482D A US3574482D A US 3574482DA US 3574482 A US3574482 A US 3574482A
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Prior art keywords
blade
end wall
plate
opening
chamber
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US793434*A
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Joseph W Savage
Henry J Brands
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General Electric Co
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General Electric Co
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    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • a cast, hollow, turbine blade has an opening in its tip end wall formed by a core pin which positioned the core in a mold as the blade was cast.
  • a plate is brazed to the inner surface of this end wall and seals this opening in a manner such that the structural integrity of the blade is not dependent on a bonded joint.
  • the present invention relates to improvements in gas turbine engines and more particularly to improved hollow blades employed in such engines.
  • Turbine blades are formed as hollow shells, not only to reduce their weight, but to provide a plenum chamber from which cooling air is discharged, through openings in the shell, into the hot gas stream.
  • the arrangement of the openings and the flow of the cooling air through the interior of the blade can take many different forms to maintain the actual metal temperature of the blade substantially cooler than the extremely high temperature of the hot gas stream which passes through the blades to drive the turbine.
  • the most advanced alloys are employed in fabricating these blades in order to permit operation in the severe environment of high temperatures and high stresses that is inherent in highperformance engines intended for the propulsion of aircraft.
  • the most effective and practical fabrication technique for forming hollow blades of such alloys is casting.
  • a core is positioned within a mold to define the hollow shell of the blade which is integrally cast with a tang employed in securing it to a turbine rotor disc.
  • This core must be supported to accurately position it within the mold.
  • One end of the core may be supported by extensions through the attaching tang which define, in the cast blade, entrance ports for cooling air.
  • the other end of the core has been supported by having the core extend beyond the tip end of the blade mold.
  • the resultant cast blade is then open at its tip end. This has necessitated attachment of an end cap, by brazing, welding or the like, in order to seal the tip end of the blade.
  • such cores have been provided with one or more'extensions to enable support of tip end of the core.
  • the resultant cast blade then has openings which have been sealed by plugs which are brazed or welded in these openings.
  • the object of the invention is to provide improved sealing mechanism for the tip ends of turbomachinery blades and, in so doing, to eliminate bonded joints as structural elements of the blades.
  • an integrally cast blade having a wall defining the tip end of the blade.
  • This wall has an opening, through which a core pin projected to support the tip end of the core, in the mold, as the blade was cast.
  • a plate overlies this opening and is secured to the inner surface of the tip wall. The tip end of the blade is thus an integral cast structure, and the core opening is sealed by the plate without reliance on any bonded joint which would be subjected to substantial stresses.
  • the opening is disposed centrally of the tip end wall and ribs project inwardly to define a recess.
  • the plate has an outline registerable with this recess to facilitate its being positioned in sealing relation.
  • the plate is bonded, as by brazing, in its sealing position to insure that it will remain in place, particularly while the rotor is at rest.
  • FIG. l illustrates a blade, with portions in section, embodying the present invention
  • FIG. 2 is a section, taken on line lI-lI in FIG. 1;
  • FIG. 3 is a view taken on line IV-IV in FIG. 1;
  • FIG. 4 is a section, along the chord, of the tip end portion of this blade, illustrating the core employed during casting of the blade.
  • the blade seen in FIG. I is an integral casting comprising a tang 12, a platform 14 and a cambered airfoil blade portion 16.
  • the blade portion is formed as a thin-walled shell defining an interior plenum chamber 18.
  • the blade would be mounted on the periphery of a rotor disc by inserting the tang in a correspondingly shaped dovetail slot. Cooling air, or other cooling fluid, in known fashion, would be directed to the base of the tang. Entrance ports 20 direct the cooling air into the plenum chamber 18. Small openings, selectively placed in the airfoil wall, discharge the cooling air along the outer surface of the blade to provide a cooling mechanism for the blade portion which projects into a hot gas stream.
  • the tip end of the cavity 18 is defined by an integrally east end wall 22.
  • An opening 24, in the end wall 22, is sealed by a plate 26.
  • the plate 26 overlies the opening 24 and is secured, or bonded, to the inner surface of the wall 24 by brazing or the like. The use of brazing assures a tight seal and further keeps the plate 26 in sealing position when the turbine blade is in operation.
  • FIG. 3 illustrates the relationship of the core to the blade during the casting operation.
  • the exterior of the blade is defined by surfaces of a conventional mold.
  • the interior chamber 18 andports 20 are defined by a core 28.
  • the portions of the core defining the ports 20 are extendedinto the mold to position the tang end of the core.
  • a core pin 30, seen in FIG. 3 extends into the mold to position the tip end of the core.
  • the plate 26 may be first coated with brazing material and then inserted through one of the ports 20, or through the opening 24, into the chamber 18. Internal ribs 32, on opposite sides of the opening 24 define a recess with which the plate 26 is registerable. After insertion in the chamber 18, it is a simple matter to position the plate in this recess, overlying the opening 24. After being so positioned, heat may be applied to melt the braze which coats the plate 26, and, upon removal of the heat, the plate will be permanently secured in its sealing position.
  • a cast, hollow, turbomachinery blade 1. A cast, hollow, turbomachinery blade:
  • the blade further comprises an integrally cast tang at the inner end of the blade;
  • the tang has at least one opening in the form of a port for admitting'cooling fluid into said chamber;
  • the plate is insertable through one of said openings to permit its introduction into said chamber and positioning on said end wall for bonding thereto.
  • a recess is formed on the inner surface of said end wall around the opening therein and the insert is registered therein, said recess facilitating positioning of said plate on said end wall.

Abstract

A cast, hollow, turbine blade has an opening in its tip end wall formed by a core pin which positioned the core in a mold as the blade was cast. A plate is brazed to the inner surface of this end wall and seals this opening in a manner such that the structural integrity of the blade is not dependent on a bonded joint.

Description

United States atet lnve ntors Joseph W. Savage;
Henry J. Brands, Cincinnati, Ohio 793,434
Jan. 23, 1969 Apr. 13, 1971 General Electric Company Appl. No. Filed Patented Assignee TURBOMACHINERY BLADES 5 Claims, 4 Drawing Figs.
U.S.Cl 416/90, 416/232 Int. Cl FOld 5/18 Field of Search 253/77 (H),
77 (l), 39.15 (B); 170/159 (M); 416/90, 95, 224, 233; 416/232 (Foreign), 248, 96, 213
[56] References Cited UNITED STATES PATENTS 2,618,120 11/1952 Papini 416/233(UX) FQREIGN PATENTS 212,964 3/1957 Australia 416/90 742,477 12/ 1955 Great Britain... 416/90 129,576 9/1950 Sweden 416/232 269,598 10/ 1 950 Switzerland 416/96 Primary ExaminerEverette A. Powell, Jr. Attorneys-Derek P. Lawrence, E. S. Lee, 111, Lee H. Sachs,
Frank L. Neuhauser and Oscar B. Waddell ABSTRACT: A cast, hollow, turbine blade has an opening in its tip end wall formed by a core pin which positioned the core in a mold as the blade was cast. A plate is brazed to the inner surface of this end wall and seals this opening in a manner such that the structural integrity of the blade is not dependent on a bonded joint.
'IURBOMACIIINERY BLADES The present invention relates to improvements in gas turbine engines and more particularly to improved hollow blades employed in such engines.
Turbine blades are formed as hollow shells, not only to reduce their weight, but to provide a plenum chamber from which cooling air is discharged, through openings in the shell, into the hot gas stream. The arrangement of the openings and the flow of the cooling air through the interior of the blade can take many different forms to maintain the actual metal temperature of the blade substantially cooler than the extremely high temperature of the hot gas stream which passes through the blades to drive the turbine.
The most advanced alloys are employed in fabricating these blades in order to permit operation in the severe environment of high temperatures and high stresses that is inherent in highperformance engines intended for the propulsion of aircraft. The most effective and practical fabrication technique for forming hollow blades of such alloys is casting. A core is positioned within a mold to define the hollow shell of the blade which is integrally cast with a tang employed in securing it to a turbine rotor disc.
The opposite ends of this core must be supported to accurately position it within the mold. One end of the core may be supported by extensions through the attaching tang which define, in the cast blade, entrance ports for cooling air. Conventionally the other end of the core has been supported by having the core extend beyond the tip end of the blade mold. The resultant cast blade is then open at its tip end. This has necessitated attachment of an end cap, by brazing, welding or the like, in order to seal the tip end of the blade. Alternatively, such cores have been provided with one or more'extensions to enable support of tip end of the core. The resultant cast blade then has openings which have been sealed by plugs which are brazed or welded in these openings.
In either case the structural integrity of the blade is dependent on joints between the blade and either the end caps or the plugs." While such approaches have been adequate in the past, bonded joints formed by welding, or the like, are not wholly reliable in the severe environment of high-performance gas turbine engines.
While the motivating environment for the present invention is in the turbine section, similar problems can also be encountered in forming and sealing the tip ends of hollow compressor blades used in a gas turbine engine. 7
Accordingly, the object of the invention is to provide improved sealing mechanism for the tip ends of turbomachinery blades and, in so doing, to eliminate bonded joints as structural elements of the blades.
These ends are attained in an integrally cast blade having a wall defining the tip end of the blade. This wall has an opening, through which a core pin projected to support the tip end of the core, in the mold, as the blade was cast. A plate overlies this opening and is secured to the inner surface of the tip wall. The tip end of the blade is thus an integral cast structure, and the core opening is sealed by the plate without reliance on any bonded joint which would be subjected to substantial stresses.
Preferably, the opening is disposed centrally of the tip end wall and ribs project inwardly to define a recess. The plate has an outline registerable with this recess to facilitate its being positioned in sealing relation. The plate is bonded, as by brazing, in its sealing position to insure that it will remain in place, particularly while the rotor is at rest.
The above and other related objects and features of the invention will be apparent from a reading of the following description of the disclosure found in the accompanying drawing and the novelty thereof pointed out in the appended claims.
In the drawing:
FIG. lillustrates a blade, with portions in section, embodying the present invention;
FIG. 2 is a section, taken on line lI-lI in FIG. 1;
FIG. 3 is a view taken on line IV-IV in FIG. 1; and
FIG. 4 is a section, along the chord, of the tip end portion of this blade, illustrating the core employed during casting of the blade.
The blade seen in FIG. I is an integral casting comprising a tang 12, a platform 14 and a cambered airfoil blade portion 16. The blade portion is formed as a thin-walled shell defining an interior plenum chamber 18.
The blade would be mounted on the periphery of a rotor disc by inserting the tang in a correspondingly shaped dovetail slot. Cooling air, or other cooling fluid, in known fashion, would be directed to the base of the tang. Entrance ports 20 direct the cooling air into the plenum chamber 18. Small openings, selectively placed in the airfoil wall, discharge the cooling air along the outer surface of the blade to provide a cooling mechanism for the blade portion which projects into a hot gas stream.
The tip end of the cavity 18 is defined by an integrally east end wall 22. An opening 24, in the end wall 22, is sealed by a plate 26. The plate 26 overlies the opening 24 and is secured, or bonded, to the inner surface of the wall 24 by brazing or the like. The use of brazing assures a tight seal and further keeps the plate 26 in sealing position when the turbine blade is in operation.
FIG. 3 illustrates the relationship of the core to the blade during the casting operation. The exterior of the blade is defined by surfaces of a conventional mold. The interior chamber 18 andports 20 are defined by a core 28. The portions of the core defining the ports 20 are extendedinto the mold to position the tang end of the core. A core pin 30, seen in FIG. 3, extends into the mold to position the tip end of the core. When the core is removed, after casting, the opening 24 exists where the core pin 30 projected into the mold.
The plate 26 may be first coated with brazing material and then inserted through one of the ports 20, or through the opening 24, into the chamber 18. Internal ribs 32, on opposite sides of the opening 24 define a recess with which the plate 26 is registerable. After insertion in the chamber 18, it is a simple matter to position the plate in this recess, overlying the opening 24. After being so positioned, heat may be applied to melt the braze which coats the plate 26, and, upon removal of the heat, the plate will be permanently secured in its sealing position.
It will be apparent that the structural integrity of the tip end of the blade is in no way dependent on the bonded joint between the plate 26 and end wall 22 when the blade is subjected to its major force loading in a direction toward its tip end, due to centrifugal forces in operation.'This is due to the fact that the-plate 26 bears against the inner surface of the tip end wall 22.
Various modifications of the described embodiment will occur to those skilled in the art within the spirit and scope of the present inventive concepts which are to be circumscribed solely by the following claims.
We claim:
1. A cast, hollow, turbomachinery blade:
having an internal chamber defined in part by an integrally east end wall at the tip end thereof;
said end wall having an opening therethrough formed by a supporting core pin during casting of the blade; and
a plate bonded to the inner surface of said end wall and overlying said opening to seal said opening.
2. A turbomachinery blade as in claim 1 wherein:
the blade further comprises an integrally cast tang at the inner end of the blade;
the tang has at least one opening in the form of a port for admitting'cooling fluid into said chamber; and
the plate is insertable through one of said openings to permit its introduction into said chamber and positioning on said end wall for bonding thereto.
3. A turbomachinery blade as in claim 2 wherein:
a recess is formed on the inner surface of said end wall around the opening therein and the insert is registered therein, said recess facilitating positioning of said plate on said end wall.
4. A method of sealing the internal chamber of a hollow, cast, turbomachinery blade having an end wall defining the outer bounds of the chamber, where said end wall has an opening therethrough, formed by a supporting core pin during 5 casting of the blade, comprising the steps of:
introducing a plate into said chamber; positioning said plate on the inner surface to said end wall,
overlying said opening; and

Claims (5)

1. A cast, hollow, turbomachinery blade: having an internal chamber defined in part by an integrally cast end wall at the tip end thereof; said end wall having an opening therethrough formed by a supporting core pin during casting of the blade; and a plate bonded to the inner surface of said end wall and overlying said opening to seal said opening.
2. A turbomachinery blade as in claim 1 wherein: the blade further comprises an integrally cast tang at the inner end of the blade; the tang has at least one opening in the form of a port for admitting cooling fluid into said chamber; and the plate is insertable through one of said openings to permit its introduction into said chamber and positioning on said end wall for bonding thereto.
3. A turbomachinery blade as in claim 2 wherein: a recess is formed on the inner surface of said end wall around the opening therein and the insert is registered therein, said recess facilitating positioning of said plate on said end wall.
4. A method of sealing the internal chamber of a hollow, cast, turbomachinery blade having an end wall defining the outer bounds of the chamber, where said end wall has an opening therethrough, formed by a supporting core pin during casting of the blade, comprising the steps of: introducing a plate into said chamber; positioning said plate on the inner surface to said end wall, overlying said opening; and bonding said plate to said end wall.
5. A method as in claim 4 comprising the further steps of: introducing a plate having brazing material thereon; subjecting the blade to heat after the plate has been so positioned to melt said braze; and removing said heat to complete the bonding of the plate to the end wall.
US793434*A 1969-01-23 1969-01-23 Turbomachinery blades Expired - Lifetime US3574482A (en)

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DE (1) DE2001983A1 (en)
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GB (1) GB1277280A (en)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3715170A (en) * 1970-12-11 1973-02-06 Gen Electric Cooled turbine blade
US3761201A (en) * 1969-04-23 1973-09-25 Avco Corp Hollow turbine blade having diffusion bonded therein
US3982851A (en) * 1975-09-02 1976-09-28 General Electric Company Tip cap apparatus
US4010531A (en) * 1975-09-02 1977-03-08 General Electric Company Tip cap apparatus and method of installation
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4487550A (en) * 1983-01-27 1984-12-11 The United States Of America As Represented By The Secretary Of The Air Force Cooled turbine blade tip closure
US4540339A (en) * 1984-06-01 1985-09-10 The United States Of America As Represented By The Secretary Of The Air Force One-piece HPTR blade squealer tip
US4589824A (en) * 1977-10-21 1986-05-20 United Technologies Corporation Rotor blade having a tip cap end closure
US6474946B2 (en) * 2001-02-26 2002-11-05 United Technologies Corporation Attachment air inlet configuration for highly loaded single crystal turbine blades
US20040056079A1 (en) * 2002-09-19 2004-03-25 Siemens Westinghouse Power Corporation Method of sealing a hollow cast member
US8622702B1 (en) 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
US20140083116A1 (en) * 2012-09-27 2014-03-27 Honeywell International Inc. Gas turbine engine components with blade tip cooling
US20160237833A1 (en) * 2015-02-18 2016-08-18 General Electric Technology Gmbh Turbine blade, set of turbine blades, and fir tree root for a turbine blade
US20170234447A1 (en) * 2016-02-12 2017-08-17 United Technologies Corporation Methods and systems for modulating airflow
US10982551B1 (en) 2012-09-14 2021-04-20 Raytheon Technologies Corporation Turbomachine blade
US11199096B1 (en) 2017-01-17 2021-12-14 Raytheon Technologies Corporation Turbomachine blade

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH269598A (en) * 1944-01-31 1950-07-15 Power Jets Res & Dev Ltd Rotor blade on turbomachine working with hot working fluid.
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
GB742477A (en) * 1952-10-31 1955-12-30 Rolls Royce Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH269598A (en) * 1944-01-31 1950-07-15 Power Jets Res & Dev Ltd Rotor blade on turbomachine working with hot working fluid.
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
GB742477A (en) * 1952-10-31 1955-12-30 Rolls Royce Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3761201A (en) * 1969-04-23 1973-09-25 Avco Corp Hollow turbine blade having diffusion bonded therein
US3715170A (en) * 1970-12-11 1973-02-06 Gen Electric Cooled turbine blade
US3982851A (en) * 1975-09-02 1976-09-28 General Electric Company Tip cap apparatus
US4010531A (en) * 1975-09-02 1977-03-08 General Electric Company Tip cap apparatus and method of installation
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4589824A (en) * 1977-10-21 1986-05-20 United Technologies Corporation Rotor blade having a tip cap end closure
US4487550A (en) * 1983-01-27 1984-12-11 The United States Of America As Represented By The Secretary Of The Air Force Cooled turbine blade tip closure
US4540339A (en) * 1984-06-01 1985-09-10 The United States Of America As Represented By The Secretary Of The Air Force One-piece HPTR blade squealer tip
US6474946B2 (en) * 2001-02-26 2002-11-05 United Technologies Corporation Attachment air inlet configuration for highly loaded single crystal turbine blades
US20040056079A1 (en) * 2002-09-19 2004-03-25 Siemens Westinghouse Power Corporation Method of sealing a hollow cast member
US6837417B2 (en) 2002-09-19 2005-01-04 Siemens Westinghouse Power Corporation Method of sealing a hollow cast member
US8622702B1 (en) 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
US10982551B1 (en) 2012-09-14 2021-04-20 Raytheon Technologies Corporation Turbomachine blade
US20140083116A1 (en) * 2012-09-27 2014-03-27 Honeywell International Inc. Gas turbine engine components with blade tip cooling
US9546554B2 (en) * 2012-09-27 2017-01-17 Honeywell International Inc. Gas turbine engine components with blade tip cooling
US20160237833A1 (en) * 2015-02-18 2016-08-18 General Electric Technology Gmbh Turbine blade, set of turbine blades, and fir tree root for a turbine blade
US10227882B2 (en) * 2015-02-18 2019-03-12 Ansaldo Energia Switzerland AG Turbine blade, set of turbine blades, and fir tree root for a turbine blade
US20170234447A1 (en) * 2016-02-12 2017-08-17 United Technologies Corporation Methods and systems for modulating airflow
US11199096B1 (en) 2017-01-17 2021-12-14 Raytheon Technologies Corporation Turbomachine blade

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BE744593A (en) 1970-07-01
GB1277280A (en) 1972-06-07
FR2028934A1 (en) 1970-10-16
DE2001983A1 (en) 1970-07-30

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