Turborotor Hybrid Gas Turbine Two-Phase Engine PUBLIC ACCESS

[+] Author Affiliations
Michael S. Rashev

Independent Research, New York, NY

Paper No. 84-GT-231, pp. V002T02A009; 11 pages
  • ASME 1984 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Amsterdam, The Netherlands, June 4–7, 1984
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7947-4
  • Copyright © 1984 by ASME


This paper analyzes the performance of an improved gas turbine engine, namely a turborotor hybrid gas turbine two-phase gas turbine engine (THGTE).

The central part of a conventional gas turbine engine is modified by introducing a number of turborotors comprising radially curved blades, to define together with the housing of the engine peripheral rotating interblade chamber-reservoirs and interblade radially curved energy-transfer passageways at their respective radially inward ends. The turborotors have the capability of energy exchange with the working fluid during the charging and expansion phases of engine operation, thus to provide a basic engine. During the expansion phase the turborotor performs a radial inflow impulse turbine function, and can be used to drive the engine’s compressor, thus to omit its conventional driving turbine.

The turborotor hybrid engine, formed by compounding the basic or turborotor engine with a conventional compressor and a power turbine has about 2 times lower specific weight and can be used as a jet propulsion turbineless engine, requiring only a nozzle to accelerate the gas products which exit the respective turborotors.

Due to its diesel mode of operation, the overall fuel efficiency is in the range of 0.58 without the use of a heat exchanger. Also, its specific power output is increased about 3 times, due to combustion of the entire amount of air passing through the compressor, under a higher fuel efficiency, if the hybrid engine is compared to the conventional gas turbine engine (CGTE).

A first approximation analysis is provided on the basis of the existing state-of-the-art and theory of the radial flow turbomachines to substantiate the basic advantages of the hybrid gas turbine engine.

Copyright © 1984 by ASME
Topics: Engines , Gas turbines
This article is only available in the PDF format.



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