Air Cooling of Gas Turbine Blades and Vanes

A numerical analysis methodology has been created to predict the heat transfer within the air cooling passages of gas turbine blades. In this paper, the turbulent flow heat convection with developed velocity and temperature fields is studied for cavities with turbulators. The influence of Coriolis forces and rotational buoyancy effects were also included. The k-equation turbulence model was employed over most of the cross section while a modified Van Driest’s version of the mixing length hypothesis is used in the near-wall sublayer. This methodology was successfully benchmarked against experimental results for air cooling passages of turbine blades. Analytical results are presented in terms of the Reynolds, Rossby and rotational Rayleigh numbers for realistic operating conditions.

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Effect of Water-Cooling Turbine Blades on Advanced Gas Turbine Power Systems

ASME 1977 International Gas Turbine Conference and Products Show ◽

10.1115/77-gt-80 ◽

1977 ◽

Author(s):

B. V. Johnson ◽

A. J. Giramonti ◽

S. J. Lehman

Keyword(s):

Power Systems ◽

Gas Turbine ◽

Pressure Ratio ◽

Turbine Blades ◽

Combined Cycle ◽

Air Cooling ◽

Water Cooling ◽

Gas Turbine Blades ◽

And Performance ◽

Cycle Efficiency

A study was conducted to determine what benefits in cycle efficiency and performance could be obtained with water-cooled gas turbine blades. Water cooling was compared against various degrees of air cooling and the ultimate limit of no cooling. Performance studies were conducted for both combined gas turbine-steam cycles and simple gas turbine cycles with temperatures at the inlet to the first turbine blade row from 1478 K (2200 F) to 1922 (3000 F) and compressor pressure ratios from 12 to 28. Results for both types of cycles indicated that absolute efficiencies 1 to 3 percentage points greater and power output per unit airflow 5 to 25 percent greater than could be obtained with water-cooled blades compared to air-cooled blades. For a given cooling scheme and pressure ratio, highest efficiencies were obtained at 1700 K (2600 F) for the simple cycle and 1922 K for the combined cycle.

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LARGE EDDY SIMULATION APPLIED TO INTERNAL FORCED-CONVECTION COOLING OF GAS-TURBINE BLADES

Proceeding of International Heat Transfer Conference 11 ◽

10.1615/ihtc11.1320 ◽

1998 ◽

Cited By ~ 2

Author(s):

Akira Murata ◽

Sadanari Mochizuki

Keyword(s):

Large Eddy Simulation ◽

Gas Turbine ◽

Forced Convection ◽

Turbine Blades ◽

Gas Turbine Blades ◽

Eddy Simulation ◽

Large Eddy ◽

Convection Cooling

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UDIMET L-605

Alloy Digest ◽

10.31399/asm.ad.co0109 ◽

2004 ◽

Vol 53 (12) ◽

Keyword(s):

Corrosion Resistance ◽

High Temperature ◽

Physical Properties ◽

Tensile Properties ◽

Gas Turbine ◽

Oxidation Resistance ◽

Turbine Blades ◽

Heat Treating ◽

Gas Turbine Blades ◽

Temperature Performance

Abstract Udimet L-605 is a high-temperature aerospace alloy with excellent strength and oxidation resistance. It is used in applications such as gas turbine blades and combustion area parts. This datasheet provides information on composition, physical properties, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, and joining. Filing Code: CO-109. Producer or source: Special Metals Corporation.

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