가스터빈 엔진 주요 변수에 따른 추력 및 비연료소모율 변화 특성 연구

Abstract

High-performance aircraft engines must satisfy such things as efficiency, economy, and reliability. The efficiency and weight ratio per thrust must be strictly matched, and in terms of reliability, the ability to continuously produce high power without failure should be provided. The specific fuel consumption is a parameter representing economic feasibility. There are various parameters that affect specific fuel consumption and thrust and Engine designers are considering thermodynamic factors such as compressor pressure ratio and turbine inlet temperature. A study on thrust and specific fuel consumption was conducted according to altitude and speed variables. The effect of the change in the cooling flow ratio of the rotor and the nozzle, which are components of the engine turbine, on the thrust and specific fuel consumption was analyzed. Thrust and specific fuel consumption were compared, when the speed and altitude parameters change with and without using the gas turbine engine afterburner. The Gasturb program was used to calculate these performances.