Accession Number:

ADA202974

Title:

Assessment, Development, and Application of Combustor Aerothermal Models

Descriptive Note:

Technical memo.

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER

Report Date:

1988-01-01

Pagination or Media Count:

21.0

Abstract:

The gas turbine combustion system design and development effort is an engineering exercise to obtain an acceptable solution to the conflicting design tradeoffs between combustion efficiency, gaseous emissions, smoke, ignition, restart, lean blowout, burner exit temperature quality, structural durability, and life cycle cost. For many years, these combustor design trade-offs have been carried out with the help of fundamental reasoning and extensive component and bench testing, backed by empirical and experience correlations. Recent advances in the capability of computational fluid dynamics CFD codes have led to their application to complex three-dimensional flows such as those in the gas turbine combustor. A number of U.S. Government and industry sponsored programs have made significant contributions to the formulation, development, and verification of an analytical combustor design methodology which will better define the aerothermal loads in a combustor, and be a valuable tool for design of future combustion systems. The contributions made by NASA Hot Section Technology HOST sponsored Aerothermal Modeling and supporting programs are described in this paper.

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE