Accession Number:

ADA169698

Title:

Ceramic Barrier Turbine Blade Demonstration.

Descriptive Note:

Final rept. Jan 84-Mar 86,

Corporate Author:

ROCKWELL INTERNATIONAL CANOGA PARK CA ROCKETDYNE DIV

Personal Author(s):

Report Date:

1986-05-01

Pagination or Media Count:

65.0

Abstract:

The next generation of gas turbine engines will operate at temperatures that exclude using uncooled metal alloys for the turbine blades. Cooling of these blades is not the optimum approach because the large coolant flow requirements will adversely affect engine efficiency. The Ceramic Barrier Turbine Blade program has successfully shown that a thermal barrier can be incorporated into the blade to shield the metal components from the hot turbine gases and greatly reduce coolant flow requirements. The principal component of this thermal barrier is a thin silicon nitride shell which envelopes a cooled metal core and retaining it with a cap at the blade tip. Loads on the shell are compressive, allowing the use of light, thin-walled sections. A novel two-layer insulatingcooling system is used to maintain the internal temperature 1000 F below the turbine operating temperature. The design features of the ceramic barrier turbine blade and the fabrication processes are described. Results of the successful spin test conducted to demonstrate concepts feasibility are presented. Keywords Silicon nitride and Mechanical properties.

Subject Categories:

  • Ceramics, Refractories and Glass
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE