TREA

Cooling air recycling for gas turbine transition duct end frame and related method

Follow

Information

  • Patent Grant
  • 6412268
  • Patent Number
    6,412,268
  • Date Filed
    Thursday, April 6, 2000
    24 years ago
  • Date Issued
    Tuesday, July 2, 2002
    22 years ago
Information
Abstract
A method of cooling a transition duct end frame in a gas turbine includes the steps of a) directing cooling air into the end frame from a region external of the transition duct and the impingement cooling sleeve; and b) redirecting the cooling air from the end frame into the annulus between the transition duct and the impingement cooling sleeve.
Description




BACKGROUND OF THE INVENTION




This invention relates to cooling of turbo machinery combustor components and specifically, to the cooling of transition ducts that connect a plurality of combustors to the first stage of a gas turbine.




In a typical arrangement, an annular array of combustors are connected to the first stage of the turbine by the transition ducts that are each shaped at one end to conform to a respective cylindrical combustor liners, and at the opposite end to conform to the turbine stage inlet. At the latter end, the transition duct has an external end frame by which the transition duct is secured to the turbine. In dry, low NOx combustion systems in the assignee's gas turbine product line, a perforated impingement cooling sleeve surrounds the transition duct, and is used to direct compressor discharge cooling air into contact with the transition duct. This cooling air eventually mixes with the fuel in the combustor.




Some of the cooling air is removed from the annulus between the transition duct and the surrounding impingement sleeve through holes in the transition duct end frame. This air, which is used to cool the end frame, dumps into the hot gas from the combustor exit just before entering the gas turbine first stage nozzle. The problem with this current method is that this cooling air by-passes the combustor, thereby effectively increasing the flame temperature and NOx emissions. On new, advanced design combustion systems, the flame temperature increase due to this combustion air loss may be as large as 8 to 10 degrees F, or equivalent to 1 to 2 ppm NOx emissions. As a result, this “by-pass air” becomes an important factor in trying to achieve gas turbine operation with single digit NOx performance.




BRIEF SUMMARY OF THE INVENTION




In accordance with this invention, transition duct end frame cooling air is reused, i.e., recirculated to the combustor, thereby lowering combustion flame temperature by about 8-10° F. More specifically, a first array of holes is drilled into the outer perimeter of the end frame and a lip or recess is milled into the face of the end frame and then sealed. The recess also communicates with a second array of holes drilled substantially axially within the end frame, and previously utilized to remove air from the annulus between the impingement sleeve and the transition duct. Now, compressor discharge air can be directed through the first array of holes to impinge on the lip milled into the face of the end frame, cooling both the lip of the end frame as well as a U-shaped strip seal component attached to the forward edge of the end frame, and then redirected through the second array of substantially axially oriented holes into the annulus between the transition duct and the impingement cooling sleeve. This air then mixes with air passing through cooling holes in the impingement sleeve, and is eventually directed to the combustion flame zone in the combustor. The substantially axially extending holes through the end frame may be turbulated to improve cooling effectiveness. The effect of reusing (instead of losing) the end frame cooling air is that the flame temperature can be reduced, thus also reducing NOx emissions.




In its broader aspects, the present invention includes a transition duct assembly for a gas turbine comprising a transition duct having opposite ends, one of the ends adapted to communicate with an inlet to a first turbine stage; an impingement cooling sleeve surrounding the transition duct with an annulus therebetween, the impingement cooling sleeve having a plurality of cooling apertures formed therein; a transition duct end frame connected to the one end of the transition duct, a forward edge of the impingement cooling sleeve received in the end frame; the end frame having a first plurality of cooling holes axially beyond the forward edge of the impingement cooling sleeve, each cooling hole communicating at the one end with space external of the impingement cooling sleeve; and a second plurality of cooling holes in the end frame, each communicating at one end with the annulus, and at an opposite end with the first plurality of cooling holes.




In another aspect, the invention relates to an end frame combustor for a gas turbine transition duct comprising a closed peripheral member adapted for attachment to a forward end of a transition duct, the peripheral member having a forward edge, a rearward edge, a top surface and a bottom surface; closed chamber about the forward edge; a first plurality of cooling bores extending from the top surface to the chamber; and a second plurality of cooling bores extending from the rearward edge to the chamber.




In still another aspect, the invention relates to a method of cooling a transition duct end frame in a gas turbine wherein an impingement cooling sleeve having a plurality of cooling apertures therein surrounds the transition duct creating an annulus therebetween, and wherein a transition duct end frame is secured to a forward edge of the transition duct, with a forward flange of the impingement sleeve also received in the end frame, the method comprising a) directing cooling air into the end frame from a region external of the transition duct and the impingement cooling sleeve; and b) redirecting the cooling air from the end frame into the annulus between the transition duct and the impingement cooling sleeve.











BRIEF DESCRIPTION OF THE DRAWINGS





FIG. 1

is a simplified cross section of a conventional transition duct located between a combustor and a first turbine stage and with the transition duct end frame omitted;





FIG. 2

is a partial cross section of the forward end of a transition duct and associated end frame in accordance with this invention; and





FIG. 3

is a partial front elevation of the transition duct end frame shown in FIG.


2


.











DETAILED DESCRIPTION OF THE INVENTION




With reference to

FIG. 1

a typical gas turbine includes a transition duct


10


by which hot combustion gases from an upstream combustor, as represented by the combustion liner


12


, are passed to the first stage inlet


14


of a turbine. The flow from the gas turbine compressor exits an axial diffuser


16


and enters into a compressor discharge case


18


. About 50% of the compressor discharge air passes through apertures


20


formed along and about a transition duct impingement cooling sleeve


22


for flow in an annular region or annulus


24


between the transition duct


10


and the radially outer transition duct impingement sleeve


22


. The remaining approximately 50% of the compressor discharge flow passes into flow sleeve holes of an upstream combustion liner cooling sleeve (not shown) and into an annulus between the cooling sleeve and the liner and eventually mixes with the air from the transition duct annulus


24


. This combined air eventually mixes with the gas turbine fuel in the combustion chamber. The transition duct typically has an end frame welded to the end that connects to the inlet of the first stage of the turbine.





FIGS. 2 and 3

illustrate a transition duct end frame assembly in accordance with this invention including a closed periphery end frame


26


that is secured to the forward edge of a transition duct


28


via weld


29


. It can be seen that a forward end of an impingement cooling sleeve


30


is formed with a radially inwardly directed flange


32


which seats within the peripheral slot


34


formed in the end frame.




A first plurality of cooling holes


36


are drilled into the outer perimeter of the end frame, forward of the slot


34


. These holes communicate with a lip or recess


38


milled into the face of the end frame continuously about the periphery thereof, the latter closed by a discrete U-strip or seal component


40


welded over the end of the frame. A second plurality of substantially axially extending cooling holes


42


are drilled in the end frame, connecting the recess


38


with the annulus


44


between the impingement sleeve


30


and the transition duct


28


. In current transition duct end frames, these are the only cooling holes in the end frame, with cooling air passing from left to right, exiting into the hot combustion gas path. Now, the cooling air flow direction is reversed so that cooling air flows from a region external of the transition duct (i.e., from the compressor discharge case


18


) into the cooling holes


36


and recess


38


and then flows from this recess into the annulus


44


via cooling holes


42


. The air exiting cooling holes


42


then mixes with air passing through the cooling holes or apertures


46


in the impingement sleeve


30


and this air is directed to the combustion flame zone.




The cooling holes


42


may be turbulated by forming surface discontinuities (such as ribs


48


or grooves or the like) to increase cooling effectiveness.




Transition duct floating and side seals (not shown) are guided by the “U” strip


40


welded over the slot or recess


34


milled into the end of the end frame.




It will be appreciated that the arrangements of cooling holes


36


and


42


are not drawn to scale, particularly in FIG.


2


. In practice, the cooling holes


42


are about 6 mils in diameter and spaced apart by about 120 mils, about the entire end frame. The cooling holes


36


may be of similar diameter and spacing although the exact size and number of both arrays of holes


36


and


42


will depend on cooling requirements.




By reversing the end frame cooling air, the flame temperature in the combustor can be reduced by 8 to 10° F., thus improving combustion efficiency and reducing NOx emissions.




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. A transition duct assembly for a gas turbine that includes a compressor and at least one combustor, the duct assembly comprising:a transition duct having opposite ends, one of said ends adapted to communicate with an inlet to a first turbine stage and another of said opposite ends adapted for connection to said at least one combustor; an impingement cooling sleeve surrounding said transition duct with an annulus therebetween, said impingement cooling sleeve having a plurality of cooling holes formed therein for receiving discharge air from the compressor and directing the discharge air towards said at least one combustor; said one end of said transition duct including an end frame, a forward edge of said impingement cooling sleeve received in said end frame; said end frame having a first plurality of cooling holes axially beyond the forward edge of said impingement cooling sleeve, each cooling hole communicating at one end with space external of said impingement cooling sleeve; and a second plurality of cooling holes in said end frame, each communication at one end with said annulus, and at an opposite end with said first plurality of cooling holes, said second plurality of holes oriented such that, in use, cooling air passing through said first plurality of cooling holes will be directed through said second plurality of cooling holes and mix with discharge air in said annulus directed towards said at least one combustor.
  • 2. The assembly of claim 1 wherein said end frame is formed with a continuous closed recess about a forward edge thereof, and further wherein said first and second pluralities of cooling holes communicate with each other through said closed recess.
  • 3. The assembly of claim 2 wherein said closed recess comprises a groove machined into said end frame and closed by a discrete seal component.
  • 4. The assembly of claim 1 wherein said second plurality of holes are turbulated.
  • 5. A method of cooling a transition duct end frame in a gas turbine with cooling air and recirculating the cooling air to a combustor of the gas turbine wherein an impingement cooling sleeve having a plurality of cooling apertures therein surrounds the transition duct creating an annulus therebetween, and wherein a forward end of said transition duct includes a transition duct end frame, with a forward flange of said impingement sleeve also received in the end frame, the method comprising:a) directing cooling air into the end frame from a region external of said transition duct and said impingement cooling sleeve; and b) redirecting said cooling air from said end frame into the annulus between the transition duct and the impingement cooling sleeve in a direction toward the combustor.
  • 6. The method of claim 5 wherein step a) is carried out by providing a first plurality of cooling holes in said end frame, first ends of said cooling holes communicating with said region.
  • 7. The method of claim 5 wherein step a) is further carried out by forming a continuous closed recess about the periphery of the end frame, with second ends of said cooling holes opening into said cooling holes opening into said closed recess.
  • 8. The method of claim 5 wherein step b) is carried out by providing a second plurality of cooling holes in said end frame extending between said closed recess and said annulus.
  • 9. The method of claim 8 and wherein step b) is further carried out by turbulating said second plurality of cooling holes.
  • 10. A method of reducing combustion flame temperature in a gas turbine that includes a compressor, at least one combustor, at least one turbine stage and a transition duct connecting said at least one combustor with said at least one turbine stage, the transition duct having an integral end frame connected to said at least one turbine stage, the method comprising:a) directing cooling air into and through the end frame from a region external of said transition duct to cool the end frame; and b) redirecting said cooling air from the end frame to said at least one combustor.
  • 11. The method of claim 10 wherein said transition duct is surrounded by an impingement cooling sleeve formed with a plurality of apertures, thus forming an annulus between the transition duct and the impingement sleeve, and further wherein discharge air from the compressor is utilized to impingement cool the transition duct via said plurality of apertures in said impingement sleeve, and further wherein, in step (b), the cooling air used to cool the end frame is redirected into the annulus for flow to said at least one combustor along with the compressor discharge air used to cool the transition duct.
  • 12. A transition duct assembly for a gas turbine that includes a compressor and at least one combustor, the duct assembly comprising:a transition duct having opposite ends, one of said ends adapted to communicate with an inlet to a first turbine stage and another of said opposite ends adapted for connection to said at least one combustor; an impingement cooling sleeve surrounding said transition duct with an annulus therebetween, said impingement cooling sleeve having a plurality of cooling holes formed therein for receiving discharge air from the compressor and directing the discharge air into said annulus and then towards said at least one combustor; a transition duct end frame integral with said one end of said transition duct, a forward edge of said impingement cooling sleeve received in said end frame; and means for supplying cooling air into and through the end frame and for redirecting said cooling air to said at least one combustor.
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.

US Referenced Citations (7)
Number Name Date Kind
3741678 Arlington et al. Jun 1973 A
3965066 Sterman et al. Jun 1976 A
4232527 Reider Nov 1980 A
4422288 Steber Dec 1983 A
4719748 Davis, Jr. et al. Jan 1988 A
4872312 Iizuka et al. Oct 1989 A
4903477 Butt Feb 1990 A
Non-Patent Literature Citations (177)
Entry
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 1, ““F” Technology—the First Half-Million Operating Hours”, H.E. Miller, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 2, “GE Heavy-Duty Gas Turbine Performance Characteristics”, F.J. Brooks, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 3, “9EC 50Hz 170-MW Class Gas Turbine”, A. S. Arrao, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 4, “MWS6001FA—An Advanced-Technology 70-MW Hz Gas Turbine”, Ramachandran et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 5, “Turbomachinery Technology Advances at Nuovo Pignone”, Benvenuti et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 6, “GE Aeroderivative Gas Turbines—Design and Operating Features”, M.W. Horner, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 7, “Advance Gas Turbine Materials and Coatings”, P.W. Schilke, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 8, “Dry Low NOx Combustion Systems for GE Heavy-Duty Turbines”, L. B. Davis, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 9, “GE Gas Turbine Combustion Flexibility”, M. A. Davi, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 10, “Gas Fuel Clean-Up System Design Considerations for GE Heavy-Duty Gas Turbines”, C. Wilkes, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 11, “Integrated Control Systems for Advanced Combined Cycles”, Chu et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 12, “Power Systems for the 21st Century “H” Gas Turbine Combined Cycles”, Paul et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 13, “Clean Coal and Heavy Oil Technologies for Gas Turbines”, D. M. Todd, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 14, “Gas Turbine Conversions, Modifications and Uprates Technology”, Stuck et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 15, “Performance and Reliability Improvements for Heavy-Duty Gas Turbines,”J.R. Johnston, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 16, “Gas Turbine Repair Technology”, Crimi et al, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 17, “Heavy Duty Turbine Operating & Maintenance Considerations”, R. F. Hoeft, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 18, “Gas Turbine Performance Monitoring and Testing”, Schmitt et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 19, “Monitoring Service Delivery System and Diangnostics”, Madej et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 20, “Steam Turbines for Large Power Applications”, Reinker et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 21, “Steam Turbines for Ultrasupercritical Power Plants”, Retzlaff et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 22, “Steam Turbine Sustained Efficiency”, P. Schofield, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 23, “Recent Advances in Steam Turbines for Industrial and Cogeneration Applications”, Leger et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 24, “Mechanical Drive Steam Turbines”, D. R. Leger, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 25, “Steam Turbines for STAG™ Combined-Cycle Power Systems”, M. Boss, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 26, “Cogeneration Application Considerations”, Fisk et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 27, “Performance and Economic Considerations of Repowering Steam Power Plants”, Stoll et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 28, “High-Power-Density™ Steam Turbine Design Evolution”, J. H. Moore, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 29, “Advances in Steam Path Technologies”, Cofer, IV, et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 30, “Upgradable Opportunities for Steam Turbines”, D. R. Dreier, Jr., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 31, “Uprate Options for Industrial Turbines”, R. C. Beck, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 32, “Thermal Performance Evaluation and Assessment of Steam Turbine Units”, P. Albert, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 33, “Advances in Welding Repair Technology” J. F. Nolan, Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 34, “Operation and Maintenance Strategies to Enhance Plant Profitability”, MacGillivray et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 35, “Generator Insitu Inspections”, D. Stanton.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 36, “Generator Upgrade and Rewind”, Halpern et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 37, “GE Combined Cycle Product Line and Performance”, Chase, et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 38, “GE Combined Cycle Experience”, Maslak et al., Aug. 1996.
“39th GE Turbine State-of-the-Art Technology Seminar”, Tab 39, “Single-Shaft Combined Cycle Power Generation Systems”, Tomlinson et al., Aug. 1996.
“Advanced Turbine System Program—Conceptual Design and Product Development”, Annual Report, Sep. 1, 1994-Aug. 31, 1995.
“Advanced Turbine Systems (ATS Program) Conceptual Design and Product Development”, Final Technical Progress Report, vol. 2—Industrial Machine, Mar. 31, 1997, Morgantown, WV.
“Advanced Turbine Systems (ATS Program), Conceptual Design and Product Development”, Final Technical Progress Report, Aug. 31, 1996, Morgantown, WV.
“Advanced Turbine Systems (ATS) Program, Phase 2, Conceptual Design and Product Development”, Yearly Technical Progress Report, Reporting Period: Aug. 25, 1993-Aug. 31, 1994.
“Advanced Turbine Systems” Annual Program Review, Preprints, Nov. 2-4, 1998, Washington, D.C. U.S. Department of Energy, Office of Industrial Technologies Federal Energy Technology Center.
“ATS Conference” Oct. 28, 1999, Slide Presentation.
“Baglan Bay Launch Site”, various articles relating to Baglan Energy Park.
“Baglan Energy Park”, Brochure.
“Commercialization”, Del Williamson, Present, Global Sales, May 8, 1998.
“Environmental, Health and Safety Assessment: ATS 7H Program (Phase 3R) Test Activities at the GE Power Systems Gas Turbine Manufacturing Facility, Greenville, SC”, Document #1753, Feb. 1998, Publication Date: Nov. 17, 1998, Report Nos. DE-FC21-95MC31176-11.
“Exhibit panels used at 1995 product introduction at PowerGen Europe”.
“Extensive Testing Program Validates High Efficiency, reliability of GE's Advanced “H” Gas Turbine Technology”, Press Information, Press Release, 96-NR14, Jun. 26, 1996, H Technology Tests/pp. 1-4.
“Extensive Testing Program Validates High Efficiency, Reliability of GE's Advanced “H” Gas Turbine Technology”, GE Introduces Advanced Gas Turbine Technology Platform: First to Reach 60% Combined-Cycle Power Plant Efficiency, Press Information, Press Release, Power-Gen Europe '95, 95-NRR15, Advanced Technology Introduction/pp. 1-6.
“Gas, Steam Turbine Work as Single Unit in GE's Advanced H Technology Combined-Cycle System”, Press Information, Press Release, 95-NR18, May 16, 1995, Advanced Technology Introduction/pp. 1-3.
“GE Breaks 60% Net Efficiency Barrier” paper, 4 pages.
“GE Business Share Technologies and Experts to Develop State-Of-The-Art Products”, Press Information, Press Release 95-NR10, May 16, 1995, GE Technology Transfer/pp. 1-3.
“General Electric ATS Program Technical Review, Phase 2 Activities”, T. Chance et al., pp. 1-4.
“General Electric's DOE/ATS H Gas Turbine Development” Advanced Turbine Systems Annual Review Meeting, Nov. 7-8, 1996, Washington, D.C., Publication Release.
“H Technology Commercialization”, 1998 MarComm Activity Recommendation, Mar., 1998.
“H Technology”, Jon Ebacher, VP, Power Gen Technology, May 8, 1998.
“H Testing Process”, Jon Ebacher, VP, Power Gen Technology, May 8, 1998.
“Heavy-Duty & Aeroderivative Products” Gas Turbines, Brochure, 1998.
“MS7001H/MS9001H Gas Turbines, gepower.com website for PowerGen Europe” Jun. 1-3 going public Jun. 15, (1995).
“New Steam Cooling System is a Key to 60% Efficiency For GE “H” Technology Combined-Cycle Systems”, Press Information, Press Release, 95-NRR16, May 16, 1995, H Technology/pp. 1-3.
“Overview of GE's H Gas Turbine Combined Cycle”, Jul. 1, 1995 to Dec. 31, 1997.
“Power Systems for the 21st Century—“H” Gas Turbine Combined Cycles”, Thomas C. Paul et al., Report.
“Power-Gen '96 Europe”, Conference Programme, Budapest, Hungary, Jun. 26-28, 1996.
“Power-Gen International”, 1998 Show Guide, Dec. 9-11, 1998, Orange County Convention Center, Orlando, Florida.
“Press Coverage following 1995 product announcement”; various newspapar clippings relating to improved generator.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Industrial Advanced Turbine Systems Program Overview”, D.W. Esbeck, p. 3-13, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “H Gas Turbine Combined Cycle”, J. Corman, p. 14-21, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Overview of Westinghouse's Advanced Turbine Systems Program”, Bannister et al., p. 22-30, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Allison Engine ATS Program Technical Review”, D. Mukavetz, p. 31-42, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Advanced Turbine Systems Program Industrial System Concept Development”, S. Gates, p. 43-63, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Advanced Turbine System Program Phase 2 Cycle Selection”, Latcovich, Jr., p. 64-69, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “General Electric ATS Program Technical Review Phase 2 Activities”, Chance et al., p. 70-74, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Technical Review of Westinghouse's Advanced Turbine Systems Program”, Diakunchak et al., p. 75-86, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Advanced Combustion Turbines and Cycles: An EPRI Perspective”, Touchton et al., p. 87-88, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Advanced Turbine Systems Annual Program Review”, William E. Koop, p. 89-92, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “The AGTSR Consortium: An Update”, Fant et al., p. 93-102, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Overview of Allison/AGTSR Interactions”, Sy A. Ali, p. 103-106, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Design Factors for Stable Lean Premix Combustion”, Richards et al., p. 107-113, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Ceramic Stationary as Turbine”, M. van Roode, p. 114-147, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “DOE/Allison Ceramic Van Effort”, Wenglarz et al., p. 148-151, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Materials/Manufacturing Element of the Advanced Turbine Systems Program”, Karnitz et al., p. 152-160, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Land-Based Turbine Casting Initiative”, Mueller et al., p. 161-170, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Turbine Airfoil Manufacturing Technology”, Kortovich, p. 171-181, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Pratt & Whitney Thermal Barrier Coatings”, Bornstein et al., p. 182-193, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “Westinhouse Thermal Barrier Coatings”, Goedjen et al., p. 194-199, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. I, “High Performance Steam Development”, Duffy et al., p. 200-220, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Lean Premixed Combustion Stabilized by Radiation Feedback and hetergeneous Catalysis”, Dibble et al., p. 221-232, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, Rayleigh/Raman/LIF Measurements in a Turbulent Lean Premixed Combustor, Nandula et al. p. 233-248, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Lean Premixed Flames for Low Nox Combustors”, Sojka et al., p. 249-275, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Functionally Gradient Materials for Thermal Barrier Coatings in Advanced Gas Turbine Systems”, Banovic et al., p. 276-280, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Advanced Turbine Cooling, Heat Transfer, and Aerodynamic Studies”, Han et al., p. 281-309, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Life Prediction of Advanced Materials for Gas Turbines Application”, Zamrik et al., p. 310-327, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Progam Review Meeting”, vol. II, “Advanced Combustion Technologies for Gas Turbine Power Plants”, Vandsburger et al., p. 328-352, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Combustion Modeling in Advanced Gas Turbine Systems”, Smoot et al., p. 353-370, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Heat Transfer in a Two-Pass Internally Ribbed Turbine Blade Coolant Channel with Cylindrical Vortex Generators”, Hibbs et al. p. 371-390, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Rotational Effects on Turbine Blade Cooling”, Govatzidakia et al., p. 391-392, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Manifold Methods for Methane Combustion”, Yang et al., p. 393-409, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Advanced Multistage Turbine Blade Aerodynamics, Performance, Cooling, and Heat Transfer”, Fleeter et al., p. 410-414, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting, vol. II”, The Role of Reactant Unmixedness, Strain Rate, and Length Scale on Premixed Combustor Performance, Samuelsen et al., p. 415-422, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Experimental and Computational Studies of Film Cooling With Compound Angle Injection”, Goldstein et al., p. 423-451, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Compatibility of Gas Turbine Materials with Steam Cooling”, Desai et al., p. 452-464, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Use of a Laser-Induced Fluorescence Thermal Imaging System for Film Cooling Heat Transfer Measurement”, M. K. Chyu, p. 465-473, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, Effects of Geometry on Slot-Jet Film Cooling Performance, Hyams et al., p. 474-496 Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Steam as Turbine Blade Coolant: Experimental Data Generation”, Wilmsen et al., p. 497-505, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Combustion Chemical Vapor Deposited Coatings for Thermal Barrier Coating Systems”, Hampikian et al., p. 506-515, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Premixed Burner Experiments: Geometry, Mixing, and Flame Structure Issues”, Gupta et al., p. 516-528, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Intercooler Flow Path for Gas Turbines: CFD Design and Experiments”, Agrawal et al., p. 529-538, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Bond Strength and Stress Measurements in Thermal Barrier Coatings”, Gell et al., p. 539-549, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Active Control of Combustion Instabilities in Low NOx Gas Turbines”, Zinn et al., p. 550-551, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Combustion Instability Modeling and Analysis”, Santoro et al., p. 552-559, Oct., 1995.
“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., p. 560-565, Oct., 1995.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, vol. II, “Heat Pipe Turbine Vane Cooling”, Langston et al., p. 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., p. 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, p. 3-16, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Power Needs in the Chemical Industry”, Keith Davidson, p. 17-26, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Advanced Turbine Systems Program Overview”, David Esbeck, p. 27-34, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Westinghouse's Advanced Turbine Systems Program”, Gerard McQuiggan, p. 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., p. 49-72, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Allison Advanced Simple Cycle Gas Turbine System”, William D. Weisbrod, p. 73-94, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “The AGTSR Industry-University Consortium”, Lawrence P. Golan, p. 95-110, 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, p. 123-156, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Combustion Modeling in Advanced Gas Turbine Systems”, Paul O. Hedman, p. 157-180, Nov., 19967.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Manifold Methods for Methane Combustion”, Stephen B. Pope, p. 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, p. 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, p. 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, p. 233-252.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, Active Control of Combustion Instabilities in Low NOx Turbines, Ben T. Zinn, p. 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, p. 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, p. 275-290, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Compatibility of Gas Turbine Materials with Steam Cooling”, Vimal Desai, p. 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, p. 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, p. 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, p. 357-370, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Improved Modeling Techniques for Turbomachinery Flow Fields”, B. Lakshiminarayana, p. 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, p. 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, p. 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, p. 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, p. 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, p. 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, p. 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, p. 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, p. 499-512, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Heat Pipe Turbine Vane Cooling”, Langston et al., p. 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, p. 535,-552 Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “ATS Materials Support”, Michael Karnitz, p. 553-576, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Land Based Turbine Casting Initiative”, Boyd A. Mueller, p. 577-592, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Turbine Airfoil Manufacturing Technology”, Charles S. Kortovich, p. 593-622, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Hot Corrosion Testing of TBS's”, Norman Bornstein, p. 623-631, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Ceramic Stationary Gas Turbine”, Mark van Roode, p. 633-658, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Western European Status of Ceramics for Gas Turbines”, Tibor Bornemisza, p. 659-670, Nov., 1996.
“Proceedings of the Advanced Turbine Systems Annual Program Review Meeting”, “Status of Ceramic Gas Turbines in Russia”, Mark van Roode, p. 671, Nov., 1996.
“Status Report: The U.S. Department 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 Electricity and Low Emissions”, Roger Schonewald and Patrick Marolda, (no date available).
“Testing Program Results Validate GE's H Gas Turbine—High Efficiency, Low Cost of Electricity 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 Nos: 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 Nos: DOE/MC/31176-10.
“Utility Advanced Turbine System (ATS) Technology Readiness Testing and Pre-Commercial Demonstration, Phase 3”, Document #486029, Oct.-Dec. 31, 1995, Publication Date, May 1, 1997, Report Nos: 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 Nos.: 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 Nos.: DOE/MC/31176-5339.
“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 Nos.: 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 Nos.: 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 Nos.: DOE/MC/31176-17.
“Utility Advanced Turbine Systems (ATS) Technology Readiness Testing and Pre-Commercial Demonstration”, Annual Technical Progress Report, Reporting Period: Jul. 1, 1995-Sep. 30, 1996.
“Utility Advanced Turbine Systems (ATS) Technology Readiness Testing”, Phase 3R, Annual Technical Progress Report, Reporting Period: Oct. 1, 1997-Sep. 30, 1998.
“Utility Advanced Turbine Systems (ATS) Technology Readiness Testing”, Document #750405, Oct. 1-Dec. 30, 1998, Publication Date: May, 1, 1999, Report Nos.: DE-FC21-95MC31176-20.
“Utility Advanced Turbine Systems (ATS) Technology Readiness Testing”, Document #1348, Apr. 1-Jun. 29, 1998, Publication Date Oct. 29, 1998, Report Nos. DE-FC21-95MC31176-18.
“Utility Advanced Turbine Systems (ATS) Technology Readiness Testing—Phase 3”, Annual Technical Progress Report, Reporting Period: Oct. 1, 1996-Sep. 30, 1997.
“Utility Advanced Turbine Systems (ATS) Technology Readiness Testing and Pre-Commercial Demonstration”, Quarterly Report, Jan. 1-Mar. 31, 1997, Document #666275, Report Nos.: DOE/MC/31176-07.
“Proceedings of the 1997 Advanced Turbine Systems”, Annual Program Review Meeting, Oct. 28-29, 1997.