THE EFFECT OF TURBINE BLADE COOLING ON EFFICIENCY OF A SIMPLE GAS TURBINE POWER PLANT

Abstract

Three conditions were investigated for the effect on thermal efficiency and specific air consumption for turbines with an infinite number of stages. The following assumptions were made: the compressor efficiency was 85%, the turbine polytropic efficiency was 88% for both the cooled and uncooled portions of the turbine, the stage efficiency was 85% for a turbine with a finite number of stages. It was concluded that turbines with design inlet temperatures of 2000 deg - 2500 deg F requiring cooling to 1000 deg F can obtain cycle efficiencies within 1 or 2 % of those obtained by turbines requiring cooling to 1500 deg F but designed with inlet temperatures of 2000 deg - 2500 deg F.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1953
Accession Number
AD0011815

Entities

People

  • W.m. Rohsenow

Organizations

  • Massachusetts Institute of Technology

Tags

DTIC Thesaurus Topics

  • Compressors
  • Cooling
  • Efficiency
  • Energy
  • Equations
  • Flow
  • Gas Turbines
  • Heat Transfer
  • High Pressure
  • High Temperature
  • Kinetic Energy
  • Materials
  • Mechanical Engineering
  • Thermal Efficiency
  • Turbine Blades
  • Turbine Components
  • Turbines

Fields of Study

  • Engineering

Readers

  • Combustion and Flow Dynamics.