Component and turbine assembly with film cooling

Details Component and turbine assembly with film cooling Component and turbine assembly with film cooling

2006-01-10

2006-01-10

Look, Edward K. (Department: 3745)

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

C416S09700R, C416S09700R, C416S235000

Reexamination Certificate

active

06984100

ABSTRACT:
A component includes a wall with a cold and a hot surface. At least one film-cooling hole extends through the wall for flowing a coolant from the cold to the hot surface. The film-cooling hole defines an exit site in the hot surface. At least one flow modifier is formed on the hot surface and is adapted to direct the coolant flowing from the film-cooling hole and out of the exit site toward the hot surface. The flow modifier extends outwards from and conforms to the hot surface. A turbine assembly includes a first and a second component that define a secondary cooling slot, which receives and guides a secondary coolant flow. At least one flow modifier is formed on a surface of one of the two components and is adapted to enhance the secondary coolant flow along at least one of the two components within the secondary coolant slot.

REFERENCES:
patent: 3864199 (1975-02-01), Meginnis
patent: 6234755 (2001-05-01), Bunker et al.
K. B. M. Q. Zaman, “Reduction of Jet Penetration in a Cross-flow by Using Tabs”, Nasa Lewis Research Center, AIAA-98-3276, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Jul. 13-15, 1998, Cleveland, OH, pp. 1-8.
L. J. S. Bradbury & A. H. Khadem, “The distortion of a jet by tabs”, J. Fluid Mech. (1975), vol. 70, part 4, pp. 801-813.
K. B. M. Q. Zaman & J. K. Foss, “The effect of vortex generators on a jet in a cross-flow”, 1997 American Institute of Physics, Phys. Fluids 9 (1), Jan. 1997, pp. 106-114.
Patent Application, Canan U. Hardwicke et al., “Systems and Methods for Determining Conditions of Articles and Methods of Making Such Systems,” Appl. No. 10/065,816, filed Nov. 22, 2002.
Ronald S. Bunker, “Film Cooling Effectiveness due to Discrete Holes within a Transverse Surface Slot,” IGTI Turbo Expo Int. Gas Turbine Conference and Exposition, Jun. 3-6, 2002, Amsterdam, GT-2002-30178, pp. 1-10.
Masir Hasan et al., “Film Cooling from a Single row of Cylindrical Angled Holes with Triangular Tabs having different Orientations,” ASME Turbo Expo 2001, Jun. 4-7, 2001, New Orleans, Louisiana, USA, 2001-GT-0124, pp. 1-8.
S.V. Ekkad et al., “Film Cooling on a Flat Surface with a Single Row of Cylindrical Angled Holes: Effect of Discrete Tabs,” HTD-vol. 366-3, ASME Heat Transfer Division—2000, vol. 3, pp. 3-12.
D. G. Hyams et al., “A Detailed Analysis of Film Cooling Physics: Part III-Streamwise Injection with Shaped Holes,” ASME, vol. 122, Jan. 2000, pp. 122-132.

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