Volvo Aero Corporation

Jan H&auml;ggander

Lars-Olof Pekkari

Jan Lundgren

Arne Boman

Mats Olofsson

Jan &Ouml;stlund

John &Auml;ngg&aring;rd

Method and arrangement for providing a liquid fuel rocket engine member ( ). The member has a load bearing wall structure ( ) having a plurality of cooling channels ( ). For improving the heat transfer, a material with a higher thermal conductivity than the load bearing wall structure ( ) is applied to the wall structure.

Rocket engine member and method for manufacturing a rocket engine member

Method and arrangement for manufacturing an outlet nozzle ( ) for use in a liquid fuel rocket engine. The nozzle forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The nozzle has a wall structure comprising a plurality of mutually adjacent cooling channels extending substantially in parallel from the inlet end ( ) of the nozzle to its outlet end ( ). The method includes providing a plurality of preprocessed profile members, each having a web and flanges in opposite directions from said web. Each profile member is machined to present a longitudinally gradually tapering width. The member is curved to conform with the wall section of the nozzle, and members are joined by welding the flanges to form a bell-shaped nozzle structure with cooling channels ( ) formed by adjacent webs and adjacent pairs of flanges.

Method for manufacturing outlet nozzles for rocket engines

The invention refers to a full-flow rocket nozzle having a longitudinal contour essentially corresponding to a parabola. For obtaining a flow separation control and also a side load reduction the invention suggests that the parabola contour shape from the point of 50% expansion ratio onwards or more distant from the throat of the nozzle is changing over into (i) strictly conical shape having an angle to the center line of between 15&deg; and 25&deg;, (ii) a slight outward curvature, i.e. implying a contour shape with positive 2 derivative of the radius r, or (iii) a slight inward curvature, i.e. with a negative 2 derivative of r but lying externally of the parabola contour, in the last case the 3 derivative of r being constantly equal to zero (0).

Rocket nozzle contour for flow separation control and side load reduction

The invention relates to a nozzle structure for rocket nozzles having a cooled nozzle wall comprising a large member of closely spaced cooling channels ( ) extending from the inlet end of the nozzle to its outlet end. To facilitate the production of the cooled nozzle wall, it is suggested according to the invention that said nozzle wall consists of several elongated panels ( ) which extend from the inlet to the outlet end of the nozzle and are joined together at their longitudinal side edges ( ) and in each of which is formed a number of said cooling channels ( ) which extend in the longitudinal direction of the panels ( ).

Nozzle structure for rocket nozzles having cooled nozzle wall

A rocket nozzle having an axial double bell shape. The nozzle includes a first bell shape, a second bell shape and an inflection point where the first bell shape and the second bell shape meet. The inflection point is located between a location at the area ratio &egr;&equals;10 and a location at 0.85&times;&egr;,of the nozzle, where &egr; is the narrowest cross-sectional area of the nozzle. The first bell shape and the second bell shape both have a contour line having an outwardly directed curvature of between 2 and 7 at the inflection point.

Controlled temperature rocket nozzle

A rocket engine nozzle with an outlet portion having a curved profile in axial section. In order to control the flow separation occurring within the nozzle outlet, the radius of the outlet portion, in axial section, varies circumferentially in length.

Growing community of inventors

Trollhättan, Sweden

Jan Häggander

Growing community of inventors

Trollhättan, Sweden

Jan H&auml;ggander

Jan Häggander