Accession Number : ADD013365

Title :   Heat Resistant Short Nozzle.

Descriptive Note : Patent, Filed 1 Oct 85, patented 21 Jul 87,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Wetzler, Dallas G ; Conley, Ralph R

Report Date : 21 Jul 1987

Pagination or Media Count : 5

Abstract : An improved nozzle structure for an engine, such as a ramjet, rocket or turbojet, which generates thrust by expulsion fo gaseous fuel combustion products along a thrust axis is described which comprises an annular wall structure defining an inlet and an outlet for the nozzle and having a contoured inner surface defining near the inlet a radially inwardly convergent annular ramp of predetermined length and convergence angle, near the outlet a radially outwardly divergent annular ramp of predetermined length and divergence angle, and a nozzle throat of predetermined diameter at the juncture of the annular ramps; a transverse web member disposed at the nozzle throat and extending diametrically of the annular wall, defining two substantially symmetrical passageways through the nozzle, having a leading edge near the inlet and trailing edge near the outlet, and having a double wedge shaped cross section symmetric with respect to a plane containing the thrust axis, the surface of the web member defining a pair of radially divergent ramps on the leading edge and extending from the inlet to the throat to the trailing edge.

Descriptors :   *HEAT RESISTANT MATERIALS, *PATENTS, *EXHAUST NOZZLES, *CARBON CARBON COMPOSITES, ANGLES, COMBUSTION PRODUCTS, CONTOURS, CONVERGENCE, EXPULSION, FUELS, GASES, INLETS, INTERNAL, LEADING EDGES, NOZZLE THROATS, NOZZLES, RAMPS, SHORT RANGE(TIME), SURFACES, THROAT, THRUST, TRAILING EDGES, WALLS, ROCKET NOZZLES, ANNULAR NOZZLES, PYROLYTIC GRAPHITE, RAMJET ENGINES, TURBOJET ENGINES

Subject Categories : Laminates and Composite Materials
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE