Shrikrishna Sane

• BE(Mech), MTech(Mech), PhD
• Consultant at Indian Institute of Technology Bombay

Gas Turbine Technology development in the past fifty years was driven by advanced technologies, such as, high performance compressors, turbine blade cooling and materials, lean burning combustors, digital control and the Combined Cycle. The technology development in the next fifty years would need different set of drivers to address the changing gl...

Simulation is a useful tool for design of a gas turbine engine, especially for control system design using hardware-in-loop simulation (HILS). The simulation must have real time engine performance prediction capabilities to be useful for HILS. The paper discusses a simulator that predicts startup to shutdown gas turbine engine operation in real tim...

A Bayesian framework is investigated for the characterization of uncertainty in gas turbine performance predictions induced by unknown/poorly known model parameters. The framework provides update of prior probabilistic knowledge of the uncertain parameters on specification of physical observations and expert judgment. However, predictions of the fr...

This investigation analyzes the calibration nonlinearity of the ball-in-vortex flow-meter designed to work on the principle of a rotating sphere in and due to a vortex flow. The comparison of this flow-meter reading with the standard flow-meter indicates the existence of different calibration regimes, bifurcated by a sharp change in slope of the ca...

A methodology to evaluate IR radiation emitted by aircraft plume and received by ground-based IR detectors is discussed. The plume IR signatures were compared with other sources such as rear fuselage and tail pipe role of the atmosphere in dictating plume IR signature levels produced by the rear fuselage and engine tailpipe. It was found that plume...

Considering the consequences of aerodynamic instabilities in the compressor on performance of gas turbine engines, serious study of these phenomena, like rotating stall and surge, is very important. Full numerical modeling of these complex phenomena is very difficult and experimental validation and tuning is necessary to build confidence in the num...

Fuel economy is a major driving factor behind the recent developments in propulsion system technology for civil transport aircraft. With increase in bypass ratio, specific fuel consumption of a propulsion system decreases with increase in propulsive efficiency. The other major advantage achieved by higher bypass ratio is reduction in noise. Thus, h...

The paper presents a CFD based model for prediction of aerodynamic instabilities like rotating stall and surge in axial flow compressors. The model is based on quasi 3D Euler equations with source terms to represent momentum and energy transfer in the rotors. The numerical results are compared with experimental data of research compressors and the...

In a mixed-stream turbofan, except for fan pressure ratio, the mission matched optimum selection of other basic cycle variables like bypass ratio, overall pressure ratio, throttle ratio, and turbine entry temperature depends upon engine-airframe interactions over the prescribed mission and the available technology level. The fan pressure ratio is d...

In a mixed-stream turbofan, except for fan pressure ratio, the mission matched optimum selection of other basic cycle variables like bypass ratio, overall pressure ratio, throttle ratio, and turbine entry temperature depends upon engine-airframe interactions over the prescribed mission and the available technology level. The fan pressure ratio is d...

This paper begins with an outline of the procedure for predicting the infrared signature emissions from the airframe, engine casing, and the plume, and their attenuation by the intervening atmosphere. These emissions are contrasted against the background, to obtain the infrared signature levels. The infrared detector's - noise equivalent flux densi...

The propulsion system has a high cost of ownership, long development period, and bears a dominant influence on aircraft mission performance. Thus identification of an optimum engine cycle right in the conceptual design, which makes the aircraft most responsive in terms of the cost as well as performance, to the specified baseline mission is the pri...

The paper presents numerical results of dynamic modeling for compressor instabilities of rotating stall and surge. The two - dimensional, incompressible, inviscid, Greitzer-Moore model (1986) has been suitably modified and the results are compared with experimental data obtained by the authors at the Propulsion Division, N.A.L., Bangalore. Comparis...

In recent times, mini and micro aerial vehicles have shown significant potential as miniature unmanned aircraft for surveillance and reconnaissance purposes. Selection of correct combination of engine and propeller is very crucial step in the design of this class of vehicles. The objective of present study is to establish measurement system and obt...

In many Multi-Disciplinary-Optimization (MDO) applications, for example conceptual design of a transport aircraft, the optimizer has to invoke several disciplinary analysis routines. Some of these could be very time and effort intensive tasks like CFD, FEM or Engine Installed Performance Estimator routine as in the present work. In such situations...