METHOD OF OBTAINING A DESIRED TEMPERATURE PROFILE IN A TURBINE ENGINE AND TURBINE ENGINE INCORPORATING THE SAME

Abstract

Undesirable high temperature gradients associated with inadequate mixing of dilution air with gases of combustion in turbines is avoided in a structure wherein dilution air is injected with a high degree of circumferential swirl through an opening (50) to the interior of an annular combustor (20) at the outlet (36) thereof which is connected to a turbine nozzle (46). The high circumferential swirl generates high "g" forces causing rapid penetration of the dilution air in the radial direction through the combustion air stream and the length of the path of the combined stream, and thus residence time and thoroughness of mixing, can be controlled through the use of a baffle (60) overlying the opening (50) to direct the dilution air countercurrently to the gases of combustion prior to introduction into the stream thereof.

Source: Google Patents

35 USC §181 Secrecy Order

Inventor

• 1JACK R. SHEKLETON

Sensitive facility: San Diego CA (SAIC/General Dynamics)

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