GATE Propulsion: Turbomachinery: Centrifugal compressors and axial turbines – Previous Year Questions
8 GATE previous year questions on Turbomachinery: Centrifugal compressors and axial turbines (Propulsion, Aerospace Engineering) with answers and explanations, from every paper.
- GATE 2021 AE Q57 – An axial turbine has rotor relative inlet and exit angles 21° and 55°, degree of reaction 0.4, blade speed 340 m/s, flow area 0.08 m² and density 0.9…
- GATE 2022 AE Q35 – A turbine stator delivers gas at 500 m/s and 70° to the turbine axis. Rotor blade speed is 250 m/s. Its leading-edge relative-flow blade angle β (one…
- GATE 2023 AE Q64 – A centrifugal compressor has inlet-root diameter 0.25 m, impeller outlet diameter 0.6 m and pressure ratio 5. Air enters at 1 atm and 25°C. Polytropic…
- GATE 2026 AE Q61 – A centrifugal compressor has a constant-width radial diffuser. The diameters at the diffuser inlet and outlet are 0.2 m and 0.3 m, respectively. The…
- GATE 2026 AE Q62 – A gas mixture at a pressure of 800 kPa and a density of 5 kg/m3 enters a turbine stage. The temperature of the gas at the nozzle exit and the stage…
- GATE 2025 AE Q35 – In a centrifugal compressor, the eye tip diameter is 10 cm. For a shaft rotational speed of 490 rotations per second, the tangential speed at the…
- GATE 2024 AE Q49 – Which of the following statements is/are TRUE for an axial turbine?
- GATE 2024 AE Q58 – A centrifugal compressor is designed to operate with air. At the leading edge of the tip of the inducer (eye of the impeller), the blade angle is 45o,…