Accession Number : AD0637052
Title : ORGANIZATION OF COMBUSTION OF HEAVY FUELS IN COMBUSTION CHAMBERS OF GAS TURBINE INSTALLATIONS.
Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
Personal Author(s) : Ermolaev, M. D.
Report Date : 13 APR 1966
Pagination or Media Count : 25
Abstract : As a result of adjustment of the process of burning black oil in the combustion chamber of an aircraft gas turbine installation, the following basic conclusions were obtained: (1) Black oil Omega-12 can be effectively burned in a gas turbine with a high heat release rate of the combustion space: Qv = 5,000,000 to 30,000,000 kcal/hr cu.m atm (abs.). The best results obtained during operation of the combustion chamber yielded a coefficient of heat liberation of 0.98-0.99 in the range Alpha = 4.5-10.5. The most effective injector, being a centrifugal two-stage unit, was fully suitable for operation on Omega-12 black oil, without atomizing air, in the range Alpha > 4 and Alpha < 15, at a fuel pressure of > 15 kg/sq cm, and black oil temperature of more than 100C. (2) In the start and low-gas regimes and during operation on lean mixtures with Alpha > 15 and with fuel pressure below 15 kg/sq cm it is necessary to use atomizing air. Consequently, the best injector for atomizing Omega-12 black oil is a combined air-centrifugal three-channel injector. (3) Omega-12 black oil fed into the injector should be heated to a temperature of not less than 100C.
Descriptors : *AIRCRAFT ENGINES, *GAS TURBINES, *FUEL OIL, COMBUSTION, COMBUSTION CHAMBERS, FUEL INJECTORS, ATOMIZATION, THERMODYNAMICS, USSR.
Subject Categories : Combustion and Ignition
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE