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! ! ! Set-5

Turbine Engines

QuestionAnswer
1.Generally, when starting a turbine engine, the starter should be disengaged a. when the ignition and fuel system are activated. b. after the engine has reached self-accelerating speed. c. only after the engine has reached full idle RPM. b
2.Which of the following factors affect the thermal efficiency of a turbine engine? 1. Turbine inlet temperature. 2. Compression ratio. 3. Ambient temperature. 4. Speed of the aircraft. 5. Turbine and compressor efficiency. 6. Altitude of the aircraft. a. 1, 2, 6. b. 1, 2, 5. c. 3, 4, 6. b
3.The stators in the turbine section of a gas turbine engine a. increase the pressure of the gas flow. b. increase the velocity of the gas flow. c. decrease the velocity of the gas flow. b
4.In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance? a. Annular. b. Can annular. c. Can. c
5.In the dual axial-flow or twin spool compressor system, the first stage turbine drives the a. N(2) compressor. b. N(1) compressor. c. N(1) and N(2) compressors. a
6.What type of turbine blade is most commonly used in aircraft jet engines? a. Impulse-reaction. b. Reaction. c. Impulse. a
7.The highest heat-to-metal contact in a jet engine is the a. turbine blades. b. turbine inlet guide vanes. c. burner cans. b
8.The procedure for removing the accumulation of dirt deposits on compressor blades is called a. field cleaning. b. the soak method. c. the purging process. a
9.An exhaust cone placed aft of the turbine in a jet engine will cause the pressure in the first part of the exhaust duct to a. increase and the velocity to increase. b. decrease and the velocity to increase. c. increase and the velocity to decrease. c
10.What are the two functional elements in a centrifugal compressor? a. Turbine and compressor. b. Impeller and diffuser. c. Bucket and expander. b
11.If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they a. cannot be used again. b. must be degaussed before use. c. are in an acceptable service condition. b
12.Where do stress rupture cracks usually appear on turbine blades? a. Across the leading or trailing edge at a right angle to the edge length. b. Across the blade root, parallel to the fir tree. c. Along the leading edge, parallel to the edge. a
13.Turbine engine components exposed to high temperatures generally may NOT be marked with 1. layout dye. 2. commercial felt tip marker. 3. wax or grease pencil. 4. chalk. 5. graphite lead pencil. a. 4 and 5. b. 3 and 5. c. 1, 2, and 3. b
14.Turbine nozzle diaphragms located on the upstream side of each turbine wheel, are used in the gas turbine engine to a. decrease the velocity of the heated gases flowing past this point. b. direct the flow of gases parallel to the vertical line of the turbine blades. c. increase the velocity of the heated gases flowing past this point. c
15.What is the profile of a turbine engine compressor blade? a. The leading edge of the blade. b. A reduced blade tip thickness. c. The curvature of the blade root. b
16.The velocity of subsonic air as it flows through a convergent nozzle a. decreases. b. remains constant. c. increases. c
17.In what section of a turbojet engine is the jet nozzle located? a. Turbine. b. Exhaust. c. Combustion. b
18.Which of the following influences the operation of an automatic fuel control unit on a turbojet engine? a. Burner pressure. b. Mixture control position. c. Exhaust gas temperature. a
19.The blending of blades and vanes in a turbine engine a. should be performed parallel to the length of the blade using smooth contours to minimize stress points. b. may sometimes be accomplished with the engine installed, ordinarily using power tools. c. is usually accomplished only at engine overhaul. a
20.The stator vanes in an axial-flow compressor a. direct air into the first stage rotor vanes at the proper angle. b. convert pressure energy into velocity energy. c. convert velocity energy into pressure energy. c
21.What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine? a. Retrim the engine. b. Perform a full power engine run to check fuel flow. c. Recalibrate the fuel nozzles. a
22.A turbine engine compressor which contains vanes on both sides of the impeller is a a. single entry axial-flow compressor. b. double entry axial-flow compressor. c. double entry centrifugal compressor. c
23.The function of the exhaust cone assembly of a turbine engine is to a. swirl and collect the exhaust gases into a single exhaust jet. b. collect the exhaust gases and act as a noise suppressor. c. straighten and collect the exhaust gases into a solid exhaust jet. c
24.The exhaust section of a turbine engine is designed to a. increase temperature, therefore increasing velocity. b. decrease temperature, therefore decreasing pressure. c. impart a high exit velocity to the exhaust gases. c
25.Who establishes mandatory replacement times for critical components of turbine engines? a. The engine manufacturer. b. The FAA. c. The operator working in conjunction with the FAA. a
Created by: sampizzuto
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