+

US20010010797A1 - Connector tube for a turbine rotor cooling circuit - Google Patents

Connector tube for a turbine rotor cooling circuit Download PDF

Info

Publication number
US20010010797A1
US20010010797A1 US09/814,045 US81404501A US2001010797A1 US 20010010797 A1 US20010010797 A1 US 20010010797A1 US 81404501 A US81404501 A US 81404501A US 2001010797 A1 US2001010797 A1 US 2001010797A1
Authority
US
United States
Prior art keywords
tubular
free end
tubular connector
tube
internal diameter
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.)
Granted
Application number
US09/814,045
Other versions
US6457934B2 (en
Inventor
Ming Li
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
Priority to US09/814,045 priority Critical patent/US6457934B2/en
Publication of US20010010797A1 publication Critical patent/US20010010797A1/en
Application granted granted Critical
Publication of US6457934B2 publication Critical patent/US6457934B2/en
Adjusted expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • This invention relates generally to land based gas turbine power plants, and specifically to a tubular connector used to radially connect axially extending cooling tubes in a gas turbine rotor cooling circuit.
  • a steam cooling circuit for a gas turbine rotor is disclosed in commonly owned U.S. Pat. No. 5,593,274. Briefly, cooling steam is supplied via a tube concentric to the rotor and then via radial passages to axially extending tubes (parallel to but radially outwardly of the rotor axis) which supply cooling steam to the buckets of one or more of the turbine stages. A similar return path is employed to remove the steam. Because of the rotating environment of the turbine rotor assembly and the centrifugal forces generated thereby, and because of thermal expansion of the various components, any radially oriented coolant tubes must be designed to accommodate relative axial and radial shifting movements where the radial tubes interface at opposite ends with the axial tube fittings.
  • This invention relates to a tube having coupling profiles at opposite ends which are particularly advantageous in the context of radial connecting tubes in a rotating environment.
  • the tubes to be coupled are substantially parallel but radially offset relative to the rotor axis.
  • the fittings which mate with the tube of this invention are in axial alignment with the radial tube.
  • references to radial vs. axial or to radially “outer” or radially “inner take into account the orientation of the tube as installed in a turbine rotor assembly.
  • References to the “upper” or “lower” ends of the tube correspond to radially outer and inner ends of the tube, respectively, relative to the rotor axis.
  • Reference to a “radial flange” on the tube is made with respect to the longitudinal center axis of the tube itself.
  • the radially outer or upper end of the tube has an enlarged radial flange (but with a constant tube ID) formed with a tapered edge, the taper extending inwardly toward the longitudinal center axis of the tube in an upward or radially outer direction.
  • This taper is part spherical in shape so that engagement with a flat conical seat formed on an axially aligned end of an elbow component attached to the radially outer axial cooling tube is substantially tangential.
  • the radially outer or upper tube end is able to “roll” in the seat in virtually any direction, thus accommodating relative shifting movement between the radially oriented tube and the axial tubes to which it is coupled while, at the same time resisting any radially outward movement which might otherwise occur due to centrifugal forces generated by rotation of the rotor.
  • the radially inner or lower end of the tube is formed as a “half-spoolie,” i.e., the lower free end of the tube is expanded to form a part toroid, formed by a part spherical surface.
  • an annular groove is formed about the tube end, while the thickness of the tube wall remains substantially constant.
  • This end of the tube is slidably received in a radially extending cylindrical bushing formed in the radially inner, axially extending tube.
  • This arrangement results in tangential line contact at the interface of the tube and a cylindrical ID of the bushing. There is no restraint on any radial movement of the tube at this end, however, (i.e.. other than friction) so that the tube can thermally expand in a radially inner direction relative to the rotor axis, even though the tube is constrained against thermal growth at the radially outer end thereof.
  • the invention relates to a tubular connector adapted to extend between two tubular components comprising a tubular body having an internal diameter, a first free end including an annular radial flange having a tapered surface adapted to engage a complementary seating surface on a first of the two tubular components, the internal diameter remaining constant through the first free end; and a second free end having an annular bulbous shape adapted to seat within a cylindrical end of a second of the two tubular components.
  • FIG. 1 is a partial side section of a gas turbine rotor assembly incorporating the connector tube of this invention.
  • FIG. 2 is a side section of the connector tube in accordance with an exemplary embodiment of the invention.
  • a turbine including a turbine rotor assembly, generally designated 10 , comprised of axially stacked components, for example, rotor wheels 12 , 14 , 16 and 18 which form portions of a four-stage exemplary turbine rotor with spacers 20 , 22 and 24 alternating between the wheels.
  • the wheel and spacer elements are held together on the rotor by a plurality of elongated, circumferentially extending bolts, only one of which is illustrated at 26 .
  • the wheels 12 , 14 , 16 and 18 mount a plurality of circumferentially spaced turbine buckets 12 a , 14 a , 16 a and 18 a , respectively.
  • nozzles 30 , 32 , 34 and 36 and respective wheels 12 , 14 , 16 and 18 comprise the stages of the turbine.
  • An aft shaft wheel 42 forms part of the rotor 10 and is bolted to the stacked wheels and spacers.
  • the aft shaft 44 houses a bore tube assembly described and illustrated in detail in co-pending U.S. patent application Ser. No. 09/216363 (Attorney Docket No. 839-540).
  • the bore tube assembly includes axially extending outer and inner tubes 48 and 50 , respectively, defining an annular steam-cooling supply passage 52 and a spent steam-cooling return passage 54 .
  • the passages 52 and 54 communicate steam to and from the outer rim of the rotor through sets of radially extending conduits or tubes 56 and 58 , respectively, which in turn communicate with corresponding sets of axially extending tubes spaced circumferentially about the rim of the rotor.
  • the steam supplied through the steam supply passage 52 and radial tubes 56 supply cooling steam to buckets 12 a and 14 a of the first and second stages, respectively, via axially extending tubes (not shown), while axial tubes (one shown at 57 ) and radial tubes 58 and return passage 54 receive the spent cooling steam from the buckets for return to a stationary or static pipe (not shown).
  • axial tubes 48 and 50 as well as axial tubes 57 are part of and rotate with the rotor assembly 10 .
  • Connector tube 58 includes a tubular body with a conventional “B-nut” 60 at its radially outer end, and a “half-spoolie” connector 62 at its opposite, radially inner end.
  • the “B-nut” 60 at the radially outer end includes a radial flange 64 and a spherically-shaped or tapered surface 66 .
  • the latter is designed to engage a flat, annular tapered surface 68 of, in this case, an axially aligned end of an elbow 70 which is connected at its opposite end to the radially outer axial tube 57 .
  • This is a conventional seal connection between adjacent tubular members, but is especially useful here, where the connector is subjected to centrifugal forces, tending to move the connector tube 56 in a radial outward direction.
  • the spherical end of the tube 58 will maintain sealing contact with the mating surface 68 of the elbow 70 , adjusting as necessary to any relative movement between the parts.
  • the B-nut 60 itself may be welded to the end of the tubular member 56 opposite the spoolie, or formed integrally therewith.
  • the tube 56 has an enlarged end due to a radiused enlargement, forming an annular, part spherical-shaped end 72 (also referred to as a part or half-spoolie) which fits inside a straight or cylindrical end or tubular bushing 74 extending radially from the radially inner axial tube 54 .
  • annular, part spherical-shaped end 72 also referred to as a part or half-spoolie
  • thermal growth of tube 58 is accommodated at the inner radial end of the tube, while any relative axial shifting motion between the inner and outer radial tubes is accommodated at the “B-nut” connection at the radially outer end of the tube.
  • the spoolie surface is coated on its exterior with a wear resistant coating.
  • a wear resistant coating e.g., a commercially available cobalt base coating alloy known as Tribaloy.

Landscapes

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

Abstract

A tubular connector adapted to extend between two tubular components comprising a tubular body having an internal diameter, a first free end including an annular radial flange having a tapered surface adapted to engage a complementary seating surface on a first of the two tubular components, the internal diameter remaining constant through the first free end; and a second free end having an annular bulbous shape adapted to seat within a cylindrical end of a second of the two tubular components.

Description

    BACKGROUND OF THE INVENTION
  • This invention relates generally to land based gas turbine power plants, and specifically to a tubular connector used to radially connect axially extending cooling tubes in a gas turbine rotor cooling circuit. [0001]
  • A steam cooling circuit for a gas turbine rotor is disclosed in commonly owned U.S. Pat. No. 5,593,274. Briefly, cooling steam is supplied via a tube concentric to the rotor and then via radial passages to axially extending tubes (parallel to but radially outwardly of the rotor axis) which supply cooling steam to the buckets of one or more of the turbine stages. A similar return path is employed to remove the steam. Because of the rotating environment of the turbine rotor assembly and the centrifugal forces generated thereby, and because of thermal expansion of the various components, any radially oriented coolant tubes must be designed to accommodate relative axial and radial shifting movements where the radial tubes interface at opposite ends with the axial tube fittings. [0002]
    • BRIEF SUMMARY OF THE INVENTION
  • This invention relates to a tube having coupling profiles at opposite ends which are particularly advantageous in the context of radial connecting tubes in a rotating environment. Specifically, the tubes to be coupled are substantially parallel but radially offset relative to the rotor axis. The fittings which mate with the tube of this invention, however, are in axial alignment with the radial tube. For purposes of this discussion, and unless otherwise explained, references to radial vs. axial or to radially “outer” or radially “inner,” take into account the orientation of the tube as installed in a turbine rotor assembly. References to the “upper” or “lower” ends of the tube correspond to radially outer and inner ends of the tube, respectively, relative to the rotor axis. Reference to a “radial flange” on the tube, however, is made with respect to the longitudinal center axis of the tube itself. [0003]
  • In one exemplary embodiment, the radially outer or upper end of the tube has an enlarged radial flange (but with a constant tube ID) formed with a tapered edge, the taper extending inwardly toward the longitudinal center axis of the tube in an upward or radially outer direction. This taper is part spherical in shape so that engagement with a flat conical seat formed on an axially aligned end of an elbow component attached to the radially outer axial cooling tube is substantially tangential. As a result, the radially outer or upper tube end is able to “roll” in the seat in virtually any direction, thus accommodating relative shifting movement between the radially oriented tube and the axial tubes to which it is coupled while, at the same time resisting any radially outward movement which might otherwise occur due to centrifugal forces generated by rotation of the rotor. [0004]
  • The radially inner or lower end of the tube is formed as a “half-spoolie,” i.e., the lower free end of the tube is expanded to form a part toroid, formed by a part spherical surface. In other words, an annular groove is formed about the tube end, while the thickness of the tube wall remains substantially constant. This end of the tube is slidably received in a radially extending cylindrical bushing formed in the radially inner, axially extending tube. This arrangement results in tangential line contact at the interface of the tube and a cylindrical ID of the bushing. There is no restraint on any radial movement of the tube at this end, however, (i.e.. other than friction) so that the tube can thermally expand in a radially inner direction relative to the rotor axis, even though the tube is constrained against thermal growth at the radially outer end thereof. [0005]
  • Accordingly, in its broader aspects, the invention relates to a tubular connector adapted to extend between two tubular components comprising a tubular body having an internal diameter, a first free end including an annular radial flange having a tapered surface adapted to engage a complementary seating surface on a first of the two tubular components, the internal diameter remaining constant through the first free end; and a second free end having an annular bulbous shape adapted to seat within a cylindrical end of a second of the two tubular components. [0006]
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a partial side section of a gas turbine rotor assembly incorporating the connector tube of this invention; and [0007]
  • FIG. 2 is a side section of the connector tube in accordance with an exemplary embodiment of the invention. [0008]
    • DETAILED DESCRIPTION OF THE INVENTION
  • Referring now to the drawings, there is illustrated a portion of a turbine, including a turbine rotor assembly, generally designated [0009] 10, comprised of axially stacked components, for example, rotor wheels 12, 14, 16 and 18 which form portions of a four-stage exemplary turbine rotor with spacers 20, 22 and 24 alternating between the wheels. The wheel and spacer elements are held together on the rotor by a plurality of elongated, circumferentially extending bolts, only one of which is illustrated at 26. The wheels 12, 14, 16 and 18 mount a plurality of circumferentially spaced turbine buckets 12 a, 14 a, 16 a and 18 a, respectively. The combination of nozzles 30, 32, 34 and 36 and respective wheels 12, 14, 16 and 18 comprise the stages of the turbine. An aft shaft wheel 42 forms part of the rotor 10 and is bolted to the stacked wheels and spacers.
  • In an advanced gas turbine designed by the assignee hereof, the [0010] aft shaft 44 houses a bore tube assembly described and illustrated in detail in co-pending U.S. patent application Ser. No. 09/216363 (Attorney Docket No. 839-540). Briefly, the bore tube assembly includes axially extending outer and inner tubes 48 and 50, respectively, defining an annular steam-cooling supply passage 52 and a spent steam-cooling return passage 54. The passages 52 and 54 communicate steam to and from the outer rim of the rotor through sets of radially extending conduits or tubes 56 and 58, respectively, which in turn communicate with corresponding sets of axially extending tubes spaced circumferentially about the rim of the rotor. The steam supplied through the steam supply passage 52 and radial tubes 56 supply cooling steam to buckets 12 a and 14 a of the first and second stages, respectively, via axially extending tubes (not shown), while axial tubes (one shown at 57) and radial tubes 58 and return passage 54 receive the spent cooling steam from the buckets for return to a stationary or static pipe (not shown). It will be appreciated that the bore tubes 48 and 50 as well as axial tubes 57 are part of and rotate with the rotor assembly 10.
  • With reference also to FIG. 2, the [0011] radial connector tubes 56, 58 accordance with an exemplary embodiment of the invention are identical and only tube 58 will be described in detail. Connector tube 58 includes a tubular body with a conventional “B-nut” 60 at its radially outer end, and a “half-spoolie” connector 62 at its opposite, radially inner end. The “B-nut” 60 at the radially outer end includes a radial flange 64 and a spherically-shaped or tapered surface 66. The latter is designed to engage a flat, annular tapered surface 68 of, in this case, an axially aligned end of an elbow 70 which is connected at its opposite end to the radially outer axial tube 57. This is a conventional seal connection between adjacent tubular members, but is especially useful here, where the connector is subjected to centrifugal forces, tending to move the connector tube 56 in a radial outward direction. In other words, the spherical end of the tube 58 will maintain sealing contact with the mating surface 68 of the elbow 70, adjusting as necessary to any relative movement between the parts. The B-nut 60 itself may be welded to the end of the tubular member 56 opposite the spoolie, or formed integrally therewith.
  • At the radially inner end, i.e., the spoolie end, the [0012] tube 56 has an enlarged end due to a radiused enlargement, forming an annular, part spherical-shaped end 72 (also referred to as a part or half-spoolie) which fits inside a straight or cylindrical end or tubular bushing 74 extending radially from the radially inner axial tube 54. In this way, thermal growth of tube 58 is accommodated at the inner radial end of the tube, while any relative axial shifting motion between the inner and outer radial tubes is accommodated at the “B-nut” connection at the radially outer end of the tube.
  • In the exemplary embodiment, the spoolie surface is coated on its exterior with a wear resistant coating. e.g., a commercially available cobalt base coating alloy known as Tribaloy. [0013]
  • 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. [0014]

Claims (10)

What is claimed is:
1. A tubular connector adapted to extend between two tubular components comprising a tubular body having an internal diameter, a first free end including an annular radial flange having a tapered surface adapted to engage a complementary seating surface on a first of said two tubular components, said internal diameter remaining constant through said first free end; and a second free end having an annular bulbous shape adapted to seat within a cylindrical end of a second of said two tubular components.
2. The tubular connector of
claim 1
 wherein said bulbous shape is provided in the form of a partial toroid.
3. The tubular connector of
claim 1
 wherein said second free end is coated on an exterior surface thereof with a wear-resistant material.
4. The tubular connector of
claim 3
 wherein said wear-resistant material comprises a cobalt-based alloy.
5. The tubular connector of
claim 1
 wherein said tapered surface is part spherical in shape.
6. In a land base turbine having a rotor assembly and plurality of stages, each stage including a wheel supporting a plurality of buckets, a cooling circuit including at least first and second axially extending tubes radially offset relative to each other, and a radially oriented tube coupling said first and second axially extending tubes, said radially oriented tube having an internal diameter, a first free end including an annular radial flange having a tapered surface adapted to engage a complementary seating surface on a first of said two tubular components, said internal diameter remaining constant through said first free end; and a second free end having an annular bulbous shape adapted to seat within a cylindrical end of a second of said two tubular components.
7. The tubular connector of
claim 1
 wherein said bulbous shape is provided in the form of a partial toroid.
8. The tubular connector of
claim 1
 wherein said second free end is coated on an exterior surface thereof with a wear-resistant material.
9. The tubular connector of
claim 8
 wherein said wear-resistant material comprises a cobalt-based alloy.
10. The tubular connector of
claim 1
 wherein said tapered surface is part spherical in shape.
US09/814,045 1999-08-27 2001-03-22 Connector tube for a turbine rotor cooling circuit Expired - Fee Related US6457934B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US09/814,045 US6457934B2 (en) 1999-08-27 2001-03-22 Connector tube for a turbine rotor cooling circuit

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US38419899A 1999-08-27 1999-08-27
US09/814,045 US6457934B2 (en) 1999-08-27 2001-03-22 Connector tube for a turbine rotor cooling circuit

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
US38419899A Division 1999-08-27 1999-08-27

Publications (2)

Publication Number Publication Date
US20010010797A1 true US20010010797A1 (en) 2001-08-02
US6457934B2 US6457934B2 (en) 2002-10-01

Family

ID=23516420

Family Applications (2)

Application Number Title Priority Date Filing Date
US09/814,045 Expired - Fee Related US6457934B2 (en) 1999-08-27 2001-03-22 Connector tube for a turbine rotor cooling circuit
US09/921,998 Expired - Lifetime US6581978B2 (en) 1999-08-27 2001-08-06 Connector tube for a turbine rotor cooling circuit

Family Applications After (1)

Application Number Title Priority Date Filing Date
US09/921,998 Expired - Lifetime US6581978B2 (en) 1999-08-27 2001-08-06 Connector tube for a turbine rotor cooling circuit

Country Status (4)

Country Link
US (2) US6457934B2 (en)
EP (1) EP1079068A3 (en)
JP (1) JP4974199B2 (en)
KR (1) KR100636439B1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6856059B2 (en) 2002-05-22 2005-02-15 General Electric Company Sealed turbine generator and method
US20120134778A1 (en) * 2010-11-29 2012-05-31 Alexander Anatolievich Khanin Axial flow gas turbine
CN106640208A (en) * 2015-10-31 2017-05-10 熵零股份有限公司 Impeller mechanism

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE512085C2 (en) * 1998-05-28 2000-01-24 Abb Ab A rotor machine arrangement
US8277170B2 (en) * 2008-05-16 2012-10-02 General Electric Company Cooling circuit for use in turbine bucket cooling
US8915701B2 (en) 2011-09-08 2014-12-23 General Electric Company Piping assembly and method for connecting inner and outer shell in turbine system
US8814222B2 (en) * 2012-05-23 2014-08-26 Solar Turbines Inc. Self-sealing tube for a gas turbine secondary air system
US10443498B2 (en) 2014-08-15 2019-10-15 United Technologies Corporation Gas turbine engine cooling fluid metering system
US10378379B2 (en) 2015-08-27 2019-08-13 General Electric Company Gas turbine engine cooling air manifolds with spoolies
US10968771B2 (en) 2017-01-12 2021-04-06 General Electric Company Method and system for ice tolerant bleed takeoff

Family Cites Families (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1321154A (en) * 1919-11-11 Train-pipe coupling
US216363A (en) 1879-06-10 Improvement in locomotive smoke-stack and spark-arrester
US683584A (en) 1901-05-22 1901-10-01 Charles Isaiah Wimmer Adjustable stovepipe-section.
GB578010A (en) 1941-11-21 1946-06-12 Frank Bernard Halford Improvements in jet propulsion plant
US2303927A (en) 1941-12-20 1942-12-01 Du Pont Coupling
US2693371A (en) * 1952-06-16 1954-11-02 Solar Aircraft Co Short flexible coupling
GB888860A (en) * 1957-02-20 1962-02-07 Wye Plastics Ltd Core plugs for hollow reels
GB886133A (en) * 1959-02-25 1962-01-03 United Aircraft Prod Joint constructions
US3178207A (en) * 1960-06-17 1965-04-13 Thiokol Chemical Corp Universal tube joint with bearing inserts
DE1218800B (en) * 1961-04-25 1966-06-08 M A N Turbo Ges Mit Beschraenk Gas turbine, in particular small gas turbine
US3339832A (en) * 1965-08-19 1967-09-05 Gen Electric Pipe connections for aircraft gas turbine engines
US3370830A (en) * 1966-12-12 1968-02-27 Gen Motors Corp Turbine cooling
US3746372A (en) * 1971-05-27 1973-07-17 Vetco Offshore Ind Inc Flexible pipe joints
US4054306A (en) * 1976-05-28 1977-10-18 Pressure Science Incorporated Tube and cylindrical surface sealing apparatus
US4371198A (en) * 1976-11-03 1983-02-01 Martin Charles F Apparatus for connecting tubular members
US4553775A (en) * 1983-04-26 1985-11-19 Pressure Science Incorporated Resilient annular seal with supporting liner
US4597596A (en) * 1984-11-07 1986-07-01 Heat Transfer Technology Limited Cylinder end seal
DE3509359A1 (en) * 1985-02-12 1986-08-14 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Thermal expansion feed-through
JPS62106193A (en) * 1985-10-31 1987-05-16 株式会社東芝 Expansion pipe joint
US4881759A (en) * 1988-01-04 1989-11-21 Lockheed Corporation All welded sound isolation flexible connection
US5064223A (en) 1989-10-06 1991-11-12 Ford Motor Company Throttle modulator assemblies and thermoplastic fluid direction tubes for insertion therein
US5098133A (en) 1990-01-31 1992-03-24 General Electric Company Tube coupling with swivelable piston
FR2665510B1 (en) 1990-08-03 1992-12-04 Fondeur Francois SEALED CONNECTION METHOD AND CORRESPONDING SEALED CONNECTION.
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components
FR2750451B1 (en) * 1996-06-27 1998-08-07 Snecma DEVICE FOR BLOWING GAS ADJUSTING GAMES IN A TURBOMACHINE
US6053701A (en) * 1997-01-23 2000-04-25 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor for steam cooling
JPH10238301A (en) * 1997-02-21 1998-09-08 Mitsubishi Heavy Ind Ltd Cooling passage of gas turbine blade
JP3442959B2 (en) * 1997-02-21 2003-09-02 三菱重工業株式会社 Gas turbine blade cooling medium passage
JP3722956B2 (en) * 1997-07-11 2005-11-30 三菱重工業株式会社 Gas turbine cooling passage joint seal structure
JP3500045B2 (en) * 1997-07-07 2004-02-23 三菱重工業株式会社 Steam cooling system for gas turbine blades
FR2766232B1 (en) * 1997-07-18 1999-08-20 Snecma CIRCULAR HOUSING COOLING OR HEATING DEVICE
US5964250A (en) * 1997-12-01 1999-10-12 General Electric Company Low leakage, articulating fluid transfer tube
US6224327B1 (en) * 1998-02-17 2001-05-01 Mitsubishi Heavy Idustries, Ltd. Steam-cooling type gas turbine
DE19817705C2 (en) * 1998-04-21 2001-02-15 Man Turbomasch Ag Ghh Borsig Extraction of cooling air from the diffuser part of a compressor in a gas turbine
US6029695A (en) 1998-07-24 2000-02-29 Logan; Michael Rotary union for transmitting a high pressure medium
US6131849A (en) * 1998-12-02 2000-10-17 Mcdonnell Douglas Helicopter Company Articulating/telescoping duct for reaction drive helicopters
US6190127B1 (en) * 1998-12-22 2001-02-20 General Electric Co. Tuning thermal mismatch between turbine rotor parts with a thermal medium

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6856059B2 (en) 2002-05-22 2005-02-15 General Electric Company Sealed turbine generator and method
US20120134778A1 (en) * 2010-11-29 2012-05-31 Alexander Anatolievich Khanin Axial flow gas turbine
US8932007B2 (en) * 2010-11-29 2015-01-13 Alstom Technology Ltd. Axial flow gas turbine
CN106640208A (en) * 2015-10-31 2017-05-10 熵零股份有限公司 Impeller mechanism

Also Published As

Publication number Publication date
EP1079068A2 (en) 2001-02-28
US20020025250A1 (en) 2002-02-28
JP2001082170A (en) 2001-03-27
KR20010049552A (en) 2001-06-15
US6581978B2 (en) 2003-06-24
US6457934B2 (en) 2002-10-01
EP1079068A3 (en) 2004-01-07
KR100636439B1 (en) 2006-10-18
JP4974199B2 (en) 2012-07-11

Similar Documents

Publication Publication Date Title
US6439841B1 (en) Turbine frame assembly
US6358001B1 (en) Turbine frame assembly
US6428272B1 (en) Bolted joint for rotor disks and method of reducing thermal gradients therein
US6792763B2 (en) Coated seal article with multiple coatings
US6220815B1 (en) Inter-stage seal retainer and assembly
EP0770810B1 (en) Expansion joint
US6457934B2 (en) Connector tube for a turbine rotor cooling circuit
EP0464050A1 (en) Fluid-tight joints.
US5024579A (en) Fully floating inlet flow guide for double-flow low pressure steam turbines
US7040666B2 (en) Full port externally gimballed joint
US5701733A (en) Double rabbet combustor mount
JPH01318703A (en) Steam turbine
JPS629089A (en) Slip-ring type expansion joint
US6422818B2 (en) Lubricating system for thermal medium delivery parts in a gas turbine
US10746057B2 (en) Variable nozzles in turbine engines and methods related thereto
US6471478B1 (en) Axial seal system for a gas turbine steam-cooled rotor
US6443699B1 (en) Bushing retention system for thermal medium cooling delivery tubes in a gas turbine rotor
US10711632B2 (en) Variable nozzles in turbine engines and methods related thereto
US6250062B1 (en) Fuel nozzle centering device and method for gas turbine combustors
US20090226315A1 (en) Steam turbine rotor and method of assembling the same
EP1074698B1 (en) A gas turbine comprising coated coolant supply tubes
US20030052457A1 (en) Pressure actuated snout sealing system for steam turbines
CN116917668A (en) Subassembly comprising means for compensating for differential expansion
CZ20002173A3 (en) Connecting pipe for cooling circuit of turbine rotor

Legal Events

Date Code Title Description
FPAY Fee payment

Year of fee payment: 4

REMI Maintenance fee reminder mailed
FPAY Fee payment

Year of fee payment: 8

SULP Surcharge for late payment

Year of fee payment: 7

REMI Maintenance fee reminder mailed
LAPS Lapse for failure to pay maintenance fees
STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362

FP Lapsed due to failure to pay maintenance fee

Effective date: 20141001

点击 这是indexloc提供的php浏览器服务，不要输入任何密码和下载