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Abstract(s)
A inflação do preço dos combustíveis e a constante pressão para a redução de emissões poluentes nas operações de voo, fez com que os motores turbohélice tenham vindo a ganhar um interesse renovado na indústria aeronáutica e o seu desenvolvimento seja, novamente, visto como uma inovação sustentável e promissora para voos de curto e médio alcance.
O objetivo desta dissertação é analisar o impacto de alguns parâmetros, como a razão de pressões (RP), a temperatura de entrada na turbina (TET), a velocidade de voo e a altitude de voo no desempenho do motor.
Neste contexto, é efetuada, no presente estudo, uma análise paramétrica construindo uma rotina de cálculo no software MATLAB, que visa perceber a influência dos parâmetros independentes, supra mencionados, no consumo específico de combustível (ESFC) e na potência propulsiva equivalente (ESHP) do motor PW150A, fabricado pela Pratt & Whitney Canada, para condições de voo cruzeiro.
Os resultados mostram que, tanto a razão de pressões como a temperatura de entrada na turbina do motor têm um impacto significativo no consumo específico do motor. Os valores críticos de melhor desempenho, obtidos para estes dois parâmetros, foram coerentes com os valores encontrados publicados, e referenciados nesta dissertação.
O mesmo não se verifica no caso das velocidades e altitudes do voo analisadas. Embora tenham um impacto considerável na potência propulsiva equivalente, a variação destes parâmetros influenciam de forma moderada o consumo de combustível do motor. Os resultados mostram ainda que, como seria esperado, é a altitudes elevadas que a aeronave beneficia do melhor desempenho do motor.
The inflation in fuel prices and the constant pressure to reduce pollutant emissions in flight operations, made the turboprop engines gain a renewed interest in the industry. Its development is again seen as a sustainable and promising innovation for short and medium range flights. The purpose of this dissertation is trying to understand the impact of some parameters such as pressure ratio (RP), turbine inlet temperature (TET), flight velocity and flight altitude in the performance of the engine. In this context, it is performed in the present study, a parametric analysis, building a calculation routine in MATLAB software. It aims to realize the influence of some of the independent parameters of the engine in the specific fuel consumption (ESFC) and Equivalent shaft horse power (ESHP) in the PW150A engine, produced by Pratt & Whitney Canada, for cruise flight conditions. The results show that both the pressure ratio and the turbine inlet temperature of the engine have a significant impact on the engines performance. The critical values for best performance obtained for these two parameters, were consistent with the values found published and referenced in this dissertation. The same does not happen to both the speed and flight altitudes analysed. Although they have a considerable impact on the equivalent shaft horse power, the variation of these parameters have a moderate influence on the engines performance. However the results show that at high flight altitudes the aircraft benefits from the engines best performance.
The inflation in fuel prices and the constant pressure to reduce pollutant emissions in flight operations, made the turboprop engines gain a renewed interest in the industry. Its development is again seen as a sustainable and promising innovation for short and medium range flights. The purpose of this dissertation is trying to understand the impact of some parameters such as pressure ratio (RP), turbine inlet temperature (TET), flight velocity and flight altitude in the performance of the engine. In this context, it is performed in the present study, a parametric analysis, building a calculation routine in MATLAB software. It aims to realize the influence of some of the independent parameters of the engine in the specific fuel consumption (ESFC) and Equivalent shaft horse power (ESHP) in the PW150A engine, produced by Pratt & Whitney Canada, for cruise flight conditions. The results show that both the pressure ratio and the turbine inlet temperature of the engine have a significant impact on the engines performance. The critical values for best performance obtained for these two parameters, were consistent with the values found published and referenced in this dissertation. The same does not happen to both the speed and flight altitudes analysed. Although they have a considerable impact on the equivalent shaft horse power, the variation of these parameters have a moderate influence on the engines performance. However the results show that at high flight altitudes the aircraft benefits from the engines best performance.
Description
Keywords
Motores - Consumo de combustível - Parâmetros Turbo-hélice - Consumo de combustível - Parâmetros Turbo-hélice - Consumo de combustível - Potência propulsiva equivalente