Abstract: A method and apparatus for increasing the operating life of a turbopump turbine by reducing the temperature of the combustion products impinging the turbine blades adjacent the roots thereof while increasing the temperature of the combustion products impinging the other portions of the turbine blades to maintain the overall temperature of the combustion products.

Abstract: Thrust chambers for liquid propellant rocket engines include three principal components. One of these components is an injector which contains a plurality of injection elements to meter the flow of propellants at a predetermined rate, and fuel to oxidizer mixture ratio, to introduce the mixture into the combustion chamber, and to cause them to be atomized within the combustion chamber so that even combustion takes place. Evolving from these injectors are tube injectors. These tube injectors have injection elements for injecting the oxidizer into the combustion chamber. The oxidizer and fuel must be metered at predetermined rates and mixture ratios in order to mix them within the combustion chamber so that combustion takes place smoothly and completely. Hence tube injectors are subject to improvement.