GB617164A - Improvements in jet propulsion plant - Google Patents

Abstract

617,164. Jet propulsion plant. SOC. RATEAU, and ANXIONNAZ, R. Nov. 16, 1945, No. 30846. Convention date, Feb. 27, 1945. [Class 110 (iii)] In a jet propulsion unit of the type consisting of an air-cooled internal-combustion reciprocating engine driving an air compressor which supplies air to a rearwardly-directed propelling nozzle, the air flowing to the nozzle is divided into two parts, one of which is canalized around the cylinders of the engine before reaching the nozzle and means are provided for imparting to said flow a supplementary pressure in order to compensate for the pressure losses of the cooling circuit. The internal - combustion reciprocating engine c, Fig. 8, drives an axial flow compressor b, the output of which is divided by a casing h into two parts, one of which flows round the cylinders d of the engine before it expands in the propelling nozzle g. This cooling air is further pressurized by supplementary rotating blades t. Other means of obtaining this supplementary pressure are described, e.g. the last row of blades of the axial flow compressor may be divided by a shroud ring p, Fig. 2, and the inner part of the blades o designed to give a higher pressure ratio or the width of the inner part of the blades made wider than the outer part. In another arrangement, the last blade wheel is provided with two sets of blades, the second of which are of smaller height and act only on the cooling air flow. If desired, fuel may be burnt in the air before it passes into the propelling nozzle g. Specification 563,427, [Group XXXIII], is referred to.