Aircraft Propulsion Technology

In: Business and Management

Submitted By seaneyd
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Unit 15 Aircraft Propulsion Technology
Outcome 1.1

1) T=m(V0 -V1) m= 1000kg/s T=1000(120-100) V0 =120m/s T=20,000N V1 =100 m/s

2) Total thrust =Thrust of core engine + thrust of fan

Thrust = Mass airflow x (bypass velocity – aircraft velocity) + Mass airflow x (exhaust velocity – aircraft velocity)

Thrust = 300 x (180-120) + 200 x (220-120) = 300 x 60 + 200 x100 = 1800 + 2000 = 38,000N

3) Cross reference to Unit 17 Gas turbine science outcome 2 assignment 2 Q1

4) Cross reference to Unit 17 Gas turbine science outcome 2 assignment 1 Q1

Outcome 3.2

Materials used in gas turbines have gone through many incremental improvements since the first practical turbines were developed in the 1940s. Most recent efforts have led to improved steel alloys for use in turbine vanes, blades, and inlet blocks. material improvements have led to an increase in rotor life and reliability.

Progress in gas turbine material development often came in the form of alternative stainless steel or metal alloys that had improved heat characteristics. Different parts of gas turbines use a variety of alloy metals, including varying quantities of cobalt, nickel, and chromium. In turbine compressors, manufacturers vary in their metals and manufacturing methods, but initial blades are often made with stainless steel because it is strong and easy to machine.

Materials in other parts of the turbine have been changed more frequently as the state of the art advanced. This is certainly the case with stationary turbine blades (or vanes). Some early stationary blade designs used welded structures in austenitic stainless steel that had excellent resistance to both corrosion and to oxidation at elevated temperatures, but which had limited strength capabilities. Some turbojets then switched to higher strength, nickel-based

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