1
Rosen George: Low noise prop-fan. United Aircraft Corporation, July 24, 1973: US3747343 (93 worldwide citation)

An air propulsor having either a fixed or a variable pitch fan with blade loadings selected from a range intermediate between aircraft propeller and fan engine designs is configured so as to retain high takeoff thrust and good high-speed efficiency while providing a large reduction in noise generati ...


2
Lohmann Robert P, Markowski Stanley J: Swirl combustor with vortex burning and mixing. United Aircraft Corporation, McCarthy Jack N, March 25, 1975: US3872664 (91 worldwide citation)

This disclosure sets forth an engine wherein the combustion section includes a combustor with a main combustion burner having a hot fluid injected thereinto from a pilot burner. A multiplicity of swirling jets of a cooler oxidizer fluid are directed into the combustor for engaging with the hot pilot ...


3
Kunz Harold Russell, Walsh Myles Alexander: Fuel cell utilizing fused thallium oxide electrolyte. United Aircraft Corporation, November 27, 1973: US3775185 (88 worldwide citation)

A fuel cell system for the direct generation of electricity from a fuel and oxidant is described employing an electrolyte containing thallium oxide. This fuel cell system will operate efficiently using air as an oxidant and impure hydrogen or a hydrocarbon as the fuel at relatively low temperatures, ...


4
Lee Richard E: Seal means for blade and shroud. United Aircraft Corporation, McCarthy Jack N, September 17, 1974: US3836279 (78 worldwide citation)

A turbine engine construction having a disc assembly with blades mounted therearound and a shroud construction for encompassing the ends of the blades. A sheet metal blade root seal is provided between the root of each blade and its cooperating slot in the disc for sealing cooling passages passing b ...


5
Emory Jr John M G, Faitani Joseph J E: Smoke reduction combustion chamber. United Aircraft Corporation, February 22, 1972: US3643430 (73 worldwide citation)

A combustion chamber either an annular or can-annular type, which substantially eliminates the production of smoke while maintaining all other performance parameters of the combustion chamber. The combustion chamber is provided with a front end configuration which substantially eliminates local fuel ...


6
Paulonis Daniel F, Duvall David Scott, Owczarski William A: Diffusion bonding utilizing transient liquid phase. United Aircraft Corporation, July 25, 1972: US3678570 (72 worldwide citation)

Diffusion bonding is effected utilizing a thin alloy interlayer which melts at the desired diffusion bonding temperature forming a transient liquid phase and which subsequently resolidifies at temperature as a result of constituent interdiffusion, continued heat treatment providing a homogeneous sol ...


7
Goward George W, Boone Donald H, Pettit Frederick S: High-temperature oxidation-resistant coating alloy. United Aircraft Corporation, August 28, 1973: US3754903 (68 worldwide citation)

A coating alloy for the gas turbine engine super-alloys is described which consists primarily of nickel, aluminum and a reactive metal such as yttrium, particularly at the composition, by weight, 14-30 percent aluminum, 0.01-0.5 percent reactive metal balance nickel. A preferred embodiment also incl ...


8
Bowers David A, Detolla Frank L: Segmented duct seal. United Aircraft Corporation, August 14, 1973: US3752598 (66 worldwide citation)

Confronting faces of a segmented duct of circular cross-section are provided with mutually opposing grooves running transverse to the front plane of the duct, the grooves each having a tapered surface, the tapered surfaces of opposing grooves being in mutually facing relationship with each other. A ...


9
Cohen Leonard S, Coulter Lawrence J: Jet penetration control. United Aircraft Corporation, August 14, 1973: US3752172 (64 worldwide citation)

The penetration of a sonic or supersonic gaseous jet injected through a bounding wall into a sonic or supersonic cross flow is controlled by modification of the approach flow boundary layer. Penetration is increased when the separation pressure is reduced by disturbing the approach flow boundary lay ...


10
Branstrom Bruce R, Huber Frank W: Turbine coolant flow system. United Aircraft Corporation, McCarthy Jack N, July 30, 1974: US3826084 (62 worldwide citation)

In a turbine engine compressed air is delivered through a diffuser to a burner section and then through a turbine section. A portion of the compressed air from said diffuser is removed by an annular center body manifold and directed by hollow struts inwardly to an annular passageway where the compre ...