GATE Propulsion: Gas turbine combustors: types, combustion and stoichiometric fuel-to-air ratio – Previous Year Questions
5 GATE previous year questions on Gas turbine combustors: types, combustion and stoichiometric fuel-to-air ratio (Propulsion, Aerospace Engineering) with answers and explanations, from every paper.
- GATE 2021 AE Q58 – A combustor receives 100 kg/s air at 600 K with cp=1000 J/(kg K). Exhaust is 1200 K with cp=1200 J/(kg K), fuel heating value 40 MJ/kg and combustion…
- GATE 2023 AE Q61 – A methane–air combustor operates at equivalence ratio =(F/A)/(F/A) stoich=0.5, with air flow 20 kg/s. Methane flow (kg/s, two decimal places) is .
- GATE 2025 AE Q33 – A gaseous fuel mixture comprising 3 moles of methane and 2 moles of ammonia is combusted in X moles of pure oxygen in stoichiometric amount. Assuming…
- GATE 2024 AE Q17 – A surrogate liquid hydrocarbon fuel, approximated as C 10H 12, is being burned in a land-based gas turbine combustor with dry air (79% N 2 and 21% O 2…
- GATE 2024 AE Q19 – In an airbreathing gas turbine engine, the combustor inlet temperature is 600 K. The heating value of the fuel is 43.4 106 J/kg. Assume C p to be 1100…