Accession Number:

AD0637052

Title:

ORGANIZATION OF COMBUSTION OF HEAVY FUELS IN COMBUSTION CHAMBERS OF GAS TURBINE INSTALLATIONS.

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1966-04-13

Pagination or Media Count:

25.0

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 kcalhr 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 kgsq 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 kgsq 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.

Subject Categories:

  • Combustion and Ignition
  • Fuels
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE