Accession Number:

ADA048551

Title:

Studies of Heat Transfer to Gas Turbine Components.

Descriptive Note:

Final rept. Jun 76-Oct 77,

Corporate Author:

CALSPAN CORP BUFFALO N Y

Personal Author(s):

• Dunn,Michael G.
• Stoddard,Frank J.

Report Date:

1977-10-01

Pagination or Media Count:

46.0

Abstract:

A 180 sector of the first stage stationary inlet nozzle of the AiResearch TFE-731-2 engine was instrumented with thin-film heat-transfer gages and experiments were performed to obtain detailed heat-transfer rate distributions. It is shown that the experimental apparatus can potentially be used to study total-pressure losses in cascades. The experimental apparatus consists of a helium-driven shock tube as a short-duration source of high-temperature high-pressure gas, driving a nozzle test-section device mounted near the exit of a primary shock-tunnel receiver tank. The nozzle test-section device consists of a forward transition section with a circular opening facing the supersonic primary nozzle flow and with the external shape of a frustum of a cone. Internal contouring is provided to transform the circular-section subsonic intake flow into one filling approximately a 180 annular segment having a geometry approximating that of the entrance to the turbine stator stage in a turbojet. Detailed measurements of static pressure in the test section and heat-transfer rate on the stator sector have been obtained and are reported herein. Author

Descriptors:

• *HEAT TRANSFER
• *TURBOFAN ENGINES
• TRANSIENTS
• HIGH TEMPERATURE
• TEST METHODS
• HIGH PRESSURE
• TEST EQUIPMENT
• AIRFOILS
• GAS DYNAMICS
• TURBINE BLADES
• MEASURING INSTRUMENTS
• STATIONARY
• HELIUM
• TEST FACILITIES
• SHOCK TUBES
• TURBINE COMPONENTS
• SHOCK TUNNELS
• GAS TURBINE NOZZLES
• INLET GUIDE VANES
• TURBINE STATORS

Subject Categories:

• Thermodynamics
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE