US3574482A - Turbomachinery blades - Google Patents

Turbomachinery blades Download PDF

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Publication number
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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US
United States
Prior art keywords
blade
end wall
plate
opening
chamber
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.)
Expired - Lifetime
Application number
US793434*A
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English (en)
Inventor
Joseph W Savage
Henry J Brands
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
Application granted granted Critical
Publication of US3574482A publication Critical patent/US3574482A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/12—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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US793434*A 1969-01-23 1969-01-23 Turbomachinery blades Expired - Lifetime US3574482A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US79343469A 1969-01-23 1969-01-23

Publications (1)

Publication Number Publication Date
US3574482A true US3574482A (en) 1971-04-13

Family

ID=25159913

Family Applications (1)

Application Number Title Priority Date Filing Date
US793434*A Expired - Lifetime US3574482A (en) 1969-01-23 1969-01-23 Turbomachinery blades

Country Status (5)

Country Link
US (1) US3574482A (enrdf_load_stackoverflow)
BE (1) BE744593A (enrdf_load_stackoverflow)
DE (1) DE2001983A1 (enrdf_load_stackoverflow)
FR (1) FR2028934A1 (enrdf_load_stackoverflow)
GB (1) GB1277280A (enrdf_load_stackoverflow)

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 (de) * 1944-01-31 1950-07-15 Power Jets Res & Dev Ltd Rotorschaufel an mit heissem Arbeitsmittel arbeitender Strömungsmaschine.
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 (de) * 1944-01-31 1950-07-15 Power Jets Res & Dev Ltd Rotorschaufel an mit heissem Arbeitsmittel arbeitender Strömungsmaschine.
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

Also Published As

Publication number Publication date
FR2028934A1 (enrdf_load_stackoverflow) 1970-10-16
DE2001983A1 (de) 1970-07-30
BE744593A (fr) 1970-07-01
GB1277280A (en) 1972-06-07

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