TREA

Connector tube for a turbine rotor cooling circuit

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Information

  • Patent Grant
  • 6457934
  • Patent Number
    6,457,934
  • Date Filed
    Thursday, March 22, 2001
    23 years ago
  • Date Issued
    Tuesday, October 1, 2002
    22 years ago
Information
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.




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.




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.




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.




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.




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.











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





FIG. 2

is a side section of the connector tube in accordance with an exemplary embodiment of the invention.











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


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 aft shaft


44


houses a bore tube assembly described and illustrated in detail in co-pending U.S. patent application Ser. No. 09/216,363 (Attorney Docket No. 839540). 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 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 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.




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.



Claims
  • 1. 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.
  • 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.
Parent Case Info

This application is a division of application Ser. No. 09/384,198, filed Aug. 27, 1999, now abandoned.

Government Interests

This invention was made with Government support under Contract No. DE-FC21-95MC31176 awarded by the Department of Energy. The Government has certain rights in this invention.

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Number Name Date Kind
683584 Wimmer Oct 1901 A
2303927 Fogg Dec 1942 A
2437385 Halford Mar 1948 A
3199294 Hagen Aug 1965 A
3339832 Duecker Sep 1967 A
3370830 Nickles et al. Feb 1968 A
5064223 Gross Nov 1991 A
5098133 Glover Mar 1992 A
5205593 Fondeur Apr 1993 A
5593274 Carreno et al. Jan 1997 A
5980201 Benoist et al. Nov 1999 A
5984637 Matsuo Nov 1999 A
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6053701 Ichiryu et al. Apr 2000 A
6149074 Friedel et al. Nov 2000 A
6190127 Schmidt Feb 2001 B1
6210104 Schonenborn Apr 2001 B1
6224327 Aoki et al. May 2001 B1
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“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Flow and Heat Transfer in Gas Turbine Disk Cavities Subject to Nonuniform External Pressure Field”, Roy et al., pp. 560-565, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Heat Pipe Turbine Vane Cooling”, Langston et al., pp. 566-572, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Improved Modeling Techniques for Turbomachinery Flow Fields”, Lakshminarayana et al., pp. 573-581, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Advanced 3D Inverse Method for Designing Turbomachine Blades”, T. Dang, p. 582, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “ATS and the Industries of the Future”, Denise Swink, p. 1, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Gas Turbine Association Agenda”, William H. Day, pp. 3-16, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Power Needs in the Chemical Industry”, Keith Davidson, pp. 17-26, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Advanced Turbine Systems Program Overview”, David Esbeck, pp. 27-34, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Westinghouse's Advanced Turbine Systems Program”, Gerard McQuiggan, pp. 35-48, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Overview of GE's H Gas Turbine Combined Cycle”, Cook et al., pp. 49-72, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Allison Advanced Simple Cycle Gas Turbine System”, William D. Weisbrod, pp. 73-94, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “The AGTSR Industry-University Consortium”, Lawrence P. Golan, pp. 95-100, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “NOX and CO Emissions Models for Gas-Fired Lean-Premixed Combustion Turbines”, A. Mellor, p. 111-122, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Methodologies for Active Mixing and Combustion Control”, Uri Vandsburger, pp. 123-156, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Combustion Modeling in Advanced Gas Turbine Systems”, Paul O. Hedman, pp. 157-180, Nov., 19967.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Manifold Methods for Methane Combustion”, Stephen B. Pope, pp. 181-188, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “The Role of Reactant Unmixedness, Strain Rate, and Length Scale on Premixed Combustor Performance”, Scott Samuelsen, pp. 189-210, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Effect of Swirl and Momentum Distribution on Temperature Distribution in Premixed Flames”, Ashwani K. Gupta, pp. 211-232, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Combustion Instability Studies Application to Land-Based Gas Turbine Combustors”, Robert J. Santoro, pp. 233-252.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Active Control of Combustion Instabilities in Low NOX Turbines”, Ben T. Zinn, pp. 253-264, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Life Prediction of Advanced Materials for Gas Turbine Application,” Sam Y. Zamrik, pp. 265-274, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Combustion Chemical Vapor Deposited Coatings for Thermal Barrier Coating Systems”, W. Brent Carter, pp. 275-290, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Compatibility of Gas Turbine Materials with Steam Cooling”, Vimal Desai, pp. 291-314, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Bond Strength and Stress Measurements in Thermal Barrier Coatings”, Maurice Gell, pp. 315-334, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Advanced Multistage Turbine Blade Aerodynamics, Performance, Cooling and Heat Transfer”, Sanford Fleeter, pp. 335-356, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Flow Characteristics of an Intercooler System for Power Generating Gas Turbines”, Ajay K. Agrawal, pp. 357-370, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Improved Modeling Techniques for Turbomachinery Flow Fields”, B. Lakshiminarayana, pp. 371-392, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Development of an Advanced 3d & Viscous Aerodynamic Design Method for Turbomachine Components in Utility and Industrial Gas Turbine Applications”, Thong Q. Dang, pp. 393-406, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Advanced Turbine Cooling, Heat Transfer, and Aerodynamic Studies”, Je-Chin Han, pp. 407-426, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Heat Transfer in a Two-Pass Internally Ribbed Turbine Blade Coolant Channel with Vortex Generators”, S. Acharya, pp. 427-446.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Experimental and Computational Studies of Film Cooling with Compound Angle Injection”, R. Goldstein, pp. 447-460, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Study of Endwall Film Cooling with a Gap Leakage Using a Thermographic Phosphor Fluorescence Imaging System”, Mingking K. Chyu, pp. 461-470, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Steam as a Turbine Blade Coolant: External Side Heat Transfer”, Abraham Engeda, pp. 471-482, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Flow and Heat Transfer in Gas Turbine Disk Cavities Subject to Nonuniform External Pressure Field”, Ramendra Roy, pp. 483-498, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Closed-Loop Mist/Steam Cooling for Advanced Turbine Systems”, Ting Wang, pp. 499-512, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Heat Pipe Turbine Vane Cooling”, Langston et al., pp. 513-534, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “EPRI's Combustion Turbine Program: Status and Future Directions”, Arthur Cohn, pp. 535-552, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “ATS Materials Suport”, Michael Karnitz, pp. 553-576, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Land Based Turbine Casting Initiative”, Boyd A. Meuller, pp. 577-592, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Turbine Airfoil Manufacturing Technology”, Charles S. Kortovich, pp. 593-622, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Hot Corrosion Testing of TBS's”, Norman Bornstein, pp. 623-631, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Ceramic Stationary Gas Turbine”, Mark van Roode, pp. 633-658, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Western European Status of Ceramics for Gas Turbines”, Tibor Bornemisza, pp. 659-670, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Status of Ceramic Gas Turbines in Russia”, Mark van Roode, pp. 671, Nov., 1996.
“Status Report: The U.S. Department of of Energy's Advanced Turbine Systems Program”, facsimile dated Nov. 7, 1996.
“Testing Program Results Validate GE's H Gas Turbine—High Efficiency, Low Cost of Eelctricity and Low Emissions”, Roger Schonewald and Patrick Marolda, (no date available).
“Testing Program Results Validate GE's Gas Turbine—High Efficiency, Low Cost of Eelctricity and Low Emissions”, Slide Presentation—working draft, (no date available).
“The Next Step In H . . . For Low Cost Per kW-Hour Power Generation”, LP-1 PGE ′98.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercialization Demonstration”, Document #486040, Oct. 1-Dec. 31, 1996, Publication Date, Jun. 1, 1997, Report Numbers: DOE/MC/31176-5628.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing—Phase 3”, Document #666274 Oct. 1, 1996-Sep. 30, 1997, Publication Date, Dec. 31, 1997, Report Numbers: DOE/MC/31176-10.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration, Phase 3”, Document #486029, Oct. 1-Dec. 31, 1995, Publication Date, May 1, 1997, Report Numbers: DOE/MC/31176 5340.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration, Phase 3”, Document #486132, Apr. 1-Jun. 30, 1976, Publication Date, Dec. 31, 1996, Report Numbers: DOE/MC/31176-5660.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration—Phase 3”, Document #587906, Jul. 1-Sep. 30, 1995, Publication Date, Dec. 31, 1995, Report Numbers: DOE/MC31176-5339.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration,” Document #666277, Apr. 1-Jun. 30, 1997, Publication Date, Dec. 31, 1997, Report Numbers: DOE/MC/31176-8.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercialization Demonstration”Jan. 1-Mar. 31, 1996, DOE/MC/31176-5338.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing: Phase 3R”, Document #756552, Apr. 1-Jun. 30, 1999, Publication Date, Sep. 1, 1999, Report Numbers: DE-FC21-95MC31176-23.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing.”, Document #656823, Jan. 1-Mar. 31, 1998, Publication Date, Aug. 1, 1998, Report Numbers: DOE/MC/31176-17.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration”, Annual Technical Progress Report, Reporting Period: Jul. 1, 1995-Sep. 30, 1996.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing”, Phase 3R, Annual Technical Progress Report, Reporting Period: Oct. 1, 1997-Sep. 30, 1998.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing”, Document #750405, Oct. 1-Dec. 30, 1998, Publication Date: May, 1, 1999, Report Numbers: DE-FC21-95MC31176-20.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing”, Document #1348, Apr. 1-Jun. 29, 1998, Publication Date Oct. 29, 1998, Report Numbers DE-FC21-95MC31176-18.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing—Phase 3”, Annual Technical Progress Report, Reporting Period: Oct. 1, 1996-Sep. 30, 1997.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration”, Quarterly Report, Jan. 1-Mar. 31, 1997, Document #666275, Report Numbers: DOE/MC/31176-07.
“Proceedings of the 1997 Advanced Turbine Systems”, Annual Program Review Meeting, Oct. 28-29, 1997.