GATE AE Axial Turbines PYQs & Answers

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Questions 1–7 of 7. Imported answers require independent review unless marked reviewed.

Topic practice 7 questionsPage 1 of 1

A gas mixture at a pressure of 800 kPa and a density of 5 kg/m

enters a turbine stage. The temperature of the gas at the nozzle exit and the stage exit are 790 K and 750 K, respectively. Assume the specific heats are constant for the gas mixture in the range of temperatures considered. The specific heat at constant pressure is 0.72 kJ/kg-K and the ratio of specific heats is 1.33. The value of the degree of reaction of the turbine stage is ________ (rounded off to 2 decimal places).

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Which of the following statements is/are TRUE for an axial turbine?

Your answerSelect all correct options. You can choose more than one.

For a fixed rotational speed, the mass flow rate increases with increase in the flow coefficient

The absolute stagnation enthalpy of the flow decreases across the nozzle row

The relative stagnation enthalpy remains unchanged through the rotor

For a fixed rotational speed, the mass flow rate remains unchanged with a change in the flow coefficient

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In a single stage turbine, the hot gases come out of stator/ nozzle at a speed of 500 m/s and at an angle of 70 degrees with the turbine axis as shown. The design speed of the rotor blade is 250 m/s at the mean blade radius. The rotor blade angle,

, at the leading edge is ________ degrees (round off to one decimal place).

Diagram for Aerospace Engineering question 35

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A single stage axial turbine has a mean blade speed of 340 m/s at design condition with blade angles at inlet and exit of the rotor being 21° and 55°, respectively. The degree of reaction at the mean radius of the rotor is equal to 0.4. The annulus area at the rotor inlet is 0.08 m² and the density of gas at the rotor inlet is 0.9 kg/m³. The flow rate through the turbine at these conditions is _________ kg/s (round off to two decimal places).

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The figure shows the T-S diagram for an axial turbine stage.

Diagram for Aerospace Engineering question 49

Assuming specific heat ratio of 1.33 for the hot gas, the isentropic efficiency of the turbine stage is _____% (round off to two decimal places).

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The combustion products of a gas turbine engine can be assumed to be a calorically perfect gas with

. The pressure ratio across the turbine stage is 0.14. The measured turbine inlet and exit stagnation temperatures are 1200 K and 900 K, respectively. The total-to-total turbine efficiency is ______ % (round off to the nearest integer).

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For a turbine stage, which one of the following losses occurs due to the turning of the wall boundary layer through an angle due to curved surface?

Your answerChoose one option.

Profile loss

Annulus loss

Tip clearance loss

Secondary flow loss

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GATE AE Axial Turbines PYQs

How to practice Axial Turbines

Question 62

Question 49

Question 35

Question 47

Question 49

Question 47

Question 18