Combustion chamber construction

Power plants – Combustion products used as motive fluid – Combined with regulation of power output feature

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60757, 60752, F02C 720

Patent

active

044804369

ABSTRACT:
A combustion chamber for use in gas turbine engines is provided with a liner formed of a high temperature material. The liner includes a plurality of panels of the material mounted by means of a lost motion mounting arrangement upon a high strength structural frame. As a result of this mounting arrangement, the liner is substantially isolated from structural forces associated with the combustion chamber, while the frame is substantially isolated from thermal stresses associated with the liner. For the purpose of supplying cooling air to the liner panels and frame and cooling air is passed into a plenum to cool the radially outward side of the panels. Transfer means are provided for directing the same air from the plenum to the liner inner surfaces in a cooling film. The liner mounting arrangement disclosed herein is particularly useful with difficult-to-weld liner materials (e.g., oxide dispersion strengthened materials), but its advantages commend its use with other materials also.

REFERENCES:
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Porter, H. B., Rocket Refractories, Navord Report 4893, Nots 1191, China Lake, Calif., 1955, pp. 9,10, 16-18, 34,35.

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