Masowe kryteria doboru parametrów dwuprzepływowego silnika odrzutowego do samolotu wielozadaniowego, dla wybranych zadań lotniczych

• Autorzy: Wygonik P.

Warianty tytułu

EN

Mass selection criteria of low bypass turbine engine parameters for different multi-purpose aircraft missions

• Konferencja: Kongres Silników Spalinowych (20-23.05.2007; Kraków, Poland)
• Języki publikacji: PL

Abstrakty

EN

Two-spool, low bypass mixed turbofan engines with afterburner are used for the power of multi-purpose aircrafts. Parameters of the engine comparative cycle (turbine inlet temperature, compression of compressors), by-pass ratio, fan compressor, (or low pressure compressor) are the most important engine parameters which determine their characteristics and construction. En engine and an aircraft form the complex dependence system, which is additionally complicated by a flight task. In order to fulfill the task there is a necessity for searching the optimum parameters for the total system. The most important equation that binds airplane and engine characteristics is mass balance equation. Accepting the constant value of the masses of the aircraft, obtaining of the maximum masses of the charge is possible at minimization of the masses of the engine and the fuel. The presented model of the masses of the engine, and the fuel consumption model which are the functions of thermodynamic parameters were described in the article. The sum of engine mass and fuel mass was called total engine-fuel mass. In the paper specific total engine mass index was introduced ( γε ). This index is equal to total engine-fuel mass divided by thrust in design point. Impact of the choice of the design point (Mach velocity and altitude H) on the total mass index of the engine and the fuel used up was presented for different airplane mission. The next problem is to find those thermodynamics parameters (compression ratio, turbine inlet total temperature, bypass ratio) which give minimum of total mass of engine and consumed fuel for different airplane missions. A very important parameter that plays the part in fuel consumption is airplane flight time. For long-lasting mission minimum γε is occurs for compression ratio near his economic value (for specific fuel consumption). For short missions minimum of γε occurs for smaller compression ratio (near 20-30), but greater than for those giving maximum specific thrust. A little change in minimum value of gS gives a big difference in compression ratio. The most important conclusion is that the best thermodynamics parameters from minimum mass criterion are less than for minimum specific fuel consumption. Specific total engine-fuel mass is a very important figure of merit for parameters optimization at the first step of aircraft engines design.

Słowa kluczowe

PL

samolot wielozadaniowy; silnik turbinowy; obieg cieplny

EN

multi-purpose aircraft; turbine engine; airframe and engine integration; thermal cycle

• Wydawca: Polskie Towarzystwo Naukowe Silników Spalinowych
• Czasopismo: Silniki Spalinowe
• Rocznik: 2007
• Tom: R. 46, nr SC1
• Strony: 302--312
• Opis fizyczny: Bibliogr. 18 poz.

Twórcy

autor

Wygonik P.

• Rzeszow University of Technology, Poland

Bibliografia

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