Complete Gas Turbine & Aircraft Propulsion Engineering

Explore gas turbine cycles with intercooling, featuring two-stage compression, intercooler cooling, and a turbine-driven generator, and analyze how reducing compressor work boosts net work and shaft power.

Explore the reheat gas turbine cycle with a reheat combustion chamber and two turbines that boost output and efficiency, and recognize higher fuel use and maintenance, plus limited aircraft suitability.

The regenerator in a gas turbine cycle uses exhaust heat to preheat the compressed air, increasing thermal efficiency and reducing the heat added in the combustor.

Explore a two-stage gas turbine cycle with intercooling, regenerator, and reheating. Learn how these features boost net work and thermal efficiency by reducing compressor work and heat input.

Combine gas turbine and steam turbine cycles to form a combined cycle power plant, using a heat recovery steam generator to convert exhaust heat into steam and drive two generators.

Compare gas turbine, steam turbine, and combined cycle efficiencies, highlighting Brayton and Rankine cycles and typical efficiencies of 30 to 40, 35 to 42, and 55 to 62 percent.

Work ratio (WR) is net turbine output after the compressor, with WR about 0.3–0.5; back work ratio (BWR) is the compressor's share, about 0.4–0.6, and WR = 1 − BWR.

Explore a simple gas turbine power plant in a single shaft arrangement. Link the compressor, air filter, combustion chamber, turbine, alternator, and starting motor on a common shaft.

Discover how an open cycle gas turbine power plant uses a two-stage compression with intercooling and a regenerator to boost efficiency, driving high- and low-pressure turbines and a generator.

Explore advanced gas turbine cycle technologies, including icr, hat, evaporative, caes, and sco2 turbine cycles, with comparisons on efficiency, water use, complexity, cost, flexibility, and environmental impact.

Explore schematics of advanced Brayton cycles, including humidified air turbine, evaporative cooler, CAES energy storage, and a closed-loop supercritical carbon dioxide Brayton cycle, highlighting heat exchange, combustion, and power generation.

Explore gas turbine engine types for aircraft propulsion and power generation, including turbojet, turbofan, turboprop, and turboshaft, plus air-breathing ramjet and scramjet concepts for supersonic and hypersonic flight.

Examine the stepwise operation of a centrifugal compressor, from air inlet and inducer blades to the impeller, diffuser, and volute, converting kinetic energy to static pressure for the combustor.

The lecture analyzes backward curved, radial, and forward curved impeller blades in centrifugal compressors, showing how outlet whirl relative to blade speed influences efficiency and diffusion losses.

Explore the Euler turbomachinery equation and the energy transfer by rotor blades in centrifugal compressors and turbines, including slip factor, blade speed, and whirl velocity effects.

Explain the power input factor phi_p as the ratio of actual to idle work in a centrifugal compressor, incorporating slip and losses to derive stagnation temperature and pressure ratios.

Derives the choking mass flow rate in gas turbine compressors by linking isentropic flow, stagnation properties (P0, T0), and Mach 1 at the throat to critical pressure ratios (0.528, 0.893).

Examine centrifugal compressor losses in gas turbine cycles, including frictional, incidence, leakage, recirculation, diffuser, and mechanical losses, and their effects on efficiency, stability, mass flow, surge tendency, and shaft power.

Observe the stepwise operation of an axial compressor, where inlet guide vanes align the flow, rotor and stator stages raise pressure, and high-pressure air enters the combustor for ignition.

Explore axial compressor fundamentals, velocity triangles, blade camber and diffusion, and derive the work input and temperature rise, including the work done factor lambda and its effect on stage performance.

The degree of reaction defines how much rotor static enthalpy rise contributes to the stage rise, linking velocity components and flow angles at 50% degree of reaction.

Explore surge, stall, and choking in gas turbine compressors, comparing axial and centrifugal types, and learn how these phenomena influence stability, efficiency, and overall cycle performance.

Explain how a combustor burns fuel with compressed air at near constant pressure to generate turbine inlet gases, outlining can, annular, and can-annular types and zones.

Explore combustor technologies for NOx reduction, including lean premixed (DLN/DLE), RQL, lean direct injection, staged and variable geometric combustors, catalytic and flameless combustion, water/steam injection, and exhaust after treatment.

Explore classification of turbines used in gas turbine systems by flow direction, energy transfer, stages, compounding, blade cooling, and learn how axial and multistage pressure‑compounding or reaction turbines are preferred.

Compare impulse and reaction turbines to explain how impulse converts pressure energy to kinetic energy in the nozzle, while reaction blends pressure changes across stator and rotor.

Explore multi-stage velocity compounding, also known as Curtiss stage, where a nozzle creates a high-velocity jet that undergoes pressure drop and expands through moving blades and guide vanes across stages.

Explore multi-stage pressure compounding, where nozzle and moving blades create partial pressure drops and higher exit velocity, distributing expansion across intermediate and low pressure stages in steam and gas turbines.

Explains a three-stage reaction turbine with fixed and moving blades, showing pressure and velocity changes and expansion in both blade types, and its efficiency in gas turbines and jet engines.

Explore axial flow gas turbines through velocity diagrams, analyzing how nozzle and rotor stages convert absolute and whirl velocities into turbine output for aircraft propulsion and power generation.

Define the degree of reaction as rotor enthalpy drop fraction; contrast impulse and reaction turbines and discuss nozzle angle effects on blade loading capacity and multi-stage design.

Explain the degree of reaction in axial reaction turbines, highlighting 50% split between stator and rotor drops, symmetric blade profiles, and the psi–phi relationships with exit angles alpha2 and beta3.

Explains turbine performance using dimensionless mass flow and blade speed parameters with pressure ratio P02, P03, illustrating choking conditions, efficiency limits, and the role of turbine inlet temperature and cooling.

Explore gas turbine materials and cooling, including nickel-based high-temperature alloys with gamma prime strengthening, thermal barrier coatings, film cooling, and internal convection cooling with blade tip clearance.

Learn how natural gas, aviation fuels such as Jet A, Jet A1, JP8, and hydrogen influence gas turbine performance through their combustion characteristics, efficiency, and emissions.

Explore gas turbine emissions, including nitrogen oxides (NOx), carbon monoxide, unburned hydrocarbons, and carbon dioxide, plus sulfur oxides, particulates, and noise, with control methods like dry low NOx and rich-quench-lean.

Explore gas turbine cycle controls that ensure safe starting sequences, reach self-sustaining speed, prevent compressor surge, and regulate temperature via governors, isochronous and droop methods, and fuel scheduling.

Apply cascade theory to axial compressors and axial turbines, reducing 3D blade flow to a 2D blade-to-blade model to analyze aerodynamic performance and stage efficiency, aiming to minimize flow separation.

Explore cascade nomenclature for compressor and turbine blades, defining aerofoil camber line (circular or parabolic), thickness distribution, leading/trailing edges, and key angles including lambda, I, theta1, theta2, and delta.

Analyze viscous flow effects in turbine and compressor cascades, highlighting wake zones, boundary-layer losses, blade wake mixing, and the resulting total pressure drop.

Explore blade efficiency in compressor and turbine cascades, linking ideal and actual static pressure changes to lift, drag, and mean flow angle, including drag-corrected formulas.