The Boeing Company

United Technologies Corporation

Pratt & Whitney Rocketdyne, Inc.

Brian Leigh Wherley

Jeffry A Fint

Douglas S Ades

Michael B Hankins

William D Romine

Frederick M Kuck

Myron L Jew

Donald G Ulmer

Alan Zachary Ullman

Steven C Fisher

Clyde D Newman

Albert D Tomassian

Amardeep Litt

A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.

Method of fabricating a rocket engine nozzle using pressure brazing

An apparatus and method for vaporizing liquid are provided which employ a plurality of rods disposed within a storage vessel that serve as the heat transfer element. While the plurality of rods are generally submerged by the liquid fuel to facilitate heat transfer and vaporization of the liquid fuel, the rods may be packed closely together such that the liquid inventory required to maintain the rods in a submerged state is substantially less than required by conventional fuel supply systems, thereby permitting the weight of a fuel supply system that incorporates the apparatus and method to be reduced while still permitting effective vaporization of the fuel.

Method and apparatus for vaporizing liquid

Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing

A combustion apparatus including a structural jacket, a forward liner, and an aft liner, and an associated method of constructing the same are provided. The structural jacket defines a passage including a first end, a second end, and a neck. The neck is positioned between and separates the first and second ends of the passage. The forward liner is positioned within the first end of the passage and has a throat fitted within the neck of the passage. The aft liner is positioned within the second end of the passage and has an upstream potion abutting the throat of the forward liner. The forward and aft liners are brazed together, and are bonded to the passage of the structural jacket, to form a longitudinal combustion chamber so that combustion of the propellant is contained and directed through the combustion chamber from the forward liner to the aft liner.

Combustion chamber having a multiple-piece liner and associated assembly method

Growing community of inventors

Chatsworth, CA, United States of America

Brian Leigh Wherley