Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...
Reexamination Certificate
1999-01-25
2001-01-16
Look, Edward K. (Department: 3745)
Fluid reaction surfaces (i.e., impellers)
With heating, cooling or thermal insulation means
Changing state mass within or fluid flow through working...
C416S001000, C416S09600A, C415S115000
Reexamination Certificate
active
06174133
ABSTRACT:
BACKGROUND OF THE INVENTION
This invention relates, generally, to airfoils and, more particularly, to a coolable airfoil blade of a machine.
Airfoils may be employed in various machines, for example, power turbines, compressors or aircraft engines. Vanes and blades are examples of airfoils. A blade, which blade may also be referred to as a “bucket” or “rotor,” may comprise an airfoil mounted to a wheel, disk or rotor, for rotation about a shaft. In addition, a vane, which vane may be referred to as a “nozzle” or “stator,” may comprise an airfoil mounted in a casing surrounding or covering the shaft about which the blade rotates. Typically, a series of blades are mounted about the wheel at a particular location along the shaft. Furthermore, a series of vanes are typically mounted upstream (relative to a general flow direction) of the series of blades, such as for maximizing efficiency of a fluid, for example gas, flow. Such an arrangement of vanes succeeded by blades may be referred to as a “stage.”
A number of stages of vanes and blades may be located in a compressor in order to compress gas, for example air, to be mixed and ignited with fuel, to be delivered to an inlet of a turbine. The turbine may include a number of stages of vanes and blades in order to extract work from the ignited gas and fuel. The fuel may comprise, for example, natural gas or oil. Further, the addition of the fuel to the compressed gas may involve a contribution of energy to the combustive reaction, which may raise the temperature of the gas to, for example, 3000 to 3500 degrees Fahrenheit. The product of this combustive reaction then flows through the turbine.
In order to withstand high temperatures produced by combustion, the airfoils in the turbine need to be cooled. Insufficient cooling results in undue stress on the airfoil and over time this stress leads or contributes to fatigue and failure of the airfoil. For example, existing cooling configurations include air-cooling, open-circuit cooling, closed-circuit cooling and film-cooling, using a cooling fluid from the compressor or an external source. These configurations, however, do not always enable effective cooling of the airfoil to increase engine efficiency. Accordingly, a need exists in the art for better or improved cooling of the airfoil to increase engine efficiency.
SUMMARY OF THE INVENTION
A coolable airfoil for exposure in a hot fluid flow of a machine portion, and process therefor. The airfoil is configured to be connectable with the machine portion and includes a peripheral portion surrounding a medial portion, and a chordwise extending pressure side joined with a chordwise extending suction side. At least a first channel is disposed in the peripheral portion of the pressure side and at least a second channel is disposed in the peripheral portion of the suction side. A flow path is formed from the machine portion and through the first and second channels. The flow path is configured to direct a coolant fluid substantially radially outward through the first channel in the peripheral portion of the pressure side and substantially radially inward through the second channel in the peripheral portion of the suction side to cool the airfoil.
REFERENCES:
patent: 4259037 (1981-03-01), Anderson
patent: 4312625 (1982-01-01), Pinaire
patent: 5165852 (1992-11-01), Lee et al.
patent: 5328331 (1994-07-01), Bunker et al.
patent: 5484258 (1996-01-01), Isburgh et al.
patent: 5611197 (1997-03-01), Bunker
James C. Corman et al., “Power Systems for the 21st Century “H” Gas Turbine Combined Cycles”.
B. Lakshminarayana, “Fluid Dynamics and Heat Transfer of Turbomachinery,” Penn State Univ., University Park, PA, John Wiley & Sons, Inc., pp. 632-639, 1996.
Joseph L. Mallardi, “From Teeth to Jet Engines,” Howmet Corp., Greenwich, CT, 1992.
GEAE Technical Book, entitled, “Jet Engines & Propulsion Systems for Engineers,” edited by T. W. Fowler, 1989., pp. 5-38 & 5-40.
General Electric Company
Look Edward K.
Patnode Patrick K.
Snyder Marvin
Woo Richard
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