Accession Number:

AD0481017

Title:

HIGH TEMPERATURE TURBINE COMPONENT DEVELOPMENT FOR USAAML SMALL GAS TURBINE ENGINE PROGRAM.

Descriptive Note:

Monthly technical rept. no. 16 for Sep 65.

Corporate Author:

CURTISS-WRIGHT CORP WOOD-RIDGE NJ WRIGHT AERONAUTICAL DIV

Personal Author(s):

Report Date:

1965-10-15

Pagination or Media Count:

28.0

Abstract:

The objective of the program is to advance and demonstrate high turbine temperature technology for small gas turbine engines. A transpiration cooled single stage axial flow turbine stage will be designed and tested to demonstrate feasibility of operation at 2500 F average turbine inlet temperature with a turbine work of 140 Btulb and a turbine airflow of 4 lbsec. Separate discussions are presented for each heading in the statement of work. In those cases where either work on a given item has been previously completed or there is no activity during the reporting period, the work statement heading is omitted.

Descriptors:

• *HIGH TEMPERATURE
• *GAS TURBINE BLADES
• GAS TURBINES
• ROTOR BLADES(TURBOMACHINERY)
• CASCADE STRUCTURES
• EVAPOTRANSPIRATION
• GAS FLOW
• AIR COOLED
• AIRFOILS
• DEGRADATION
• VAPORIZATION
• THERMOCOUPLES

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE