Work

Experimental heat transfer and flow results of a chordwise-finned turbine vane with impingement, film, and convection cooling

Year: 1972

Type: article

Abstract: Experimental heat transfer data are presented for a vane tested in a turbojet engine at turbine inlet gas temperatures to 1644 K (2500 F), coolant temperatures to 700 K (800 F), and coolant-to-gas flow ratios to 0.187. Methods are presented for correlating heat transfer data and obtaining coolant flow distribution through the vane. Calculated and measured coolant flow distributions and vane metal temperatures are compared.

Source: NASA Technical Reports Server (NASA)

Authors: J. W. Gauntner, J. Michael Lane, R. P. Dengler, Robert O Hickel

Institution: Glenn Research Center

Language: English

Topic: Turbomachinery Performance and Optimization

Subfield: Aerospace Engineering

Field: Engineering

Domain: Physical Sciences

SDG: Affordable and clean energy

Open Access status: green

OpenAlex ID: W228740341

FWCI: 13.12

Cites: 7

Cited by: 8

Related to: 10