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Actor Zeppo Marx patented a "Cardiac Pulse Rate Monitor" in 1969.
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| Number | Title | Issue Date |
| 4408957 | Supersonic blading Supersonic rotor blading in an axial-flow fan or compressor employs blades such that shock waves originating on a blade are canceled at the intersection of the wave and the surface of an adjacent blade by virtue of a blade configuration such that the shoc... | 10/11/1983 |
| 4226084 | Ducted fan engine exhaust mixer A turbofan engine has an exhaust arrangement for the bypassed air and turbine exhaust gases providing for mixing of the two before a common propulsion nozzle. The turbine exhaust gas is directed to a number of circumferentially spaced exhausts, the outlet... | 10/07/1980 |
| 4137708 | Jet propulsion A jet propulsion engine and a method of operating a jet propulsion engine for propulsion of an aircraft over a wide range of speed from zero to supersonic. The engine is a turbofan type with a duct burner and with separate variable exhausts from the duct ... | 02/06/1979 |
| 4004056 | Porous laminated sheet A porous laminated sheet adapted to be cooled by air flowing through the sheet from a rear face to a front face and to discharge the air through outlets in the front face at an angle to the normal to the surface. It is particularly adapted for use as a wa... | 01/18/1977 |
| 3999883 | Variable turbomachine stator A turbine nozzle has a row of vanes each rotatable about an axis extending spanwise of the vane. Each vane is rotated by a shaft which extends through one shroud of the stator vane stage. The free end of each vane is sealed by a flexible seal ring structu... | 12/28/1976 |
| 3999374 | Automotive gas turbine control A gas turbine power plant, particularly adapted for powering motor vehicles. The engine includes a gas generator made up of a compressor, combustion apparatus, and a turbine driving the compressor. It also includes a power turbine energized by the flow fr... | 12/28/1976 |
| 3999373 | Automotive gas turbine control A gas turbine power plant, particularly adapted for powering motor vehicles. The engine includes a gas generator made up of a compressor, combustion apparatus, and a turbine driving the compressor. It also includes a power turbine energized by the flow fr... | 12/28/1976 |
| 3992128 | Variable diffuser A diffuser for a centrifugal compressor has an annular array of vanes which are movable to vary the configuration of the diffusing passages between the vanes. Each vane includes a first leaf pivoted adjacent the leading edge of the vane and a second leaf ... | 11/16/1976 |
| 3990231 | Interconnections between ceramic rings permitting relative radial movement A combustion liner for a gas turbine combustion apparatus is composed of a series of ceramic wall rings coaxially aligned from the upstream to the downstream end of the liner. The ceramic rings are connected so as to be free to expand radially relative to... | 11/09/1976 |
| 3990638 | Radiation suppression The exhaust duct of a turbojet engine, which is annular with an enlarged plug or bullet at the exhaust end, includes an arrangement of the outer wall to block direct sight of the turbine of the engine through the exhaust duct. There are two rows of inward... | 11/09/1976 |
| 3984701 | Torquemeter circuit A circuit for generating a potential indicative of torque. The circuit responds to the phase angle between the AC signals generated by two generating coils or magnetoelectric pickups, each excited by a toothed wheel. The two toothed wheels are connected t... | 10/05/1976 |
| 3984193 | Radial-flow turbomachine A radial-flow turbomachine (centrifugal compressor or centripetal turbine) is provided with a lip extending along the free edge of each rotor blade from the inlet to the outlet end of the blade. The lip extends from the pressure face of the blade and serv... | 10/05/1976 |
| 3981623 | Turbomachine rotor stage A compressor or turbine rotor stage includes a wheel with a circumferential slot for retention of the roots of blades mounted on the wheel. Each side of the rim of the wheel is approximately symmetrical about a line parallel to the axis of rotation of the... | 09/21/1976 |
| 3981142 | Ceramic combustion liner A combustion liner for a gas turbine combustion apparatus has a wall of ceramic material. To minimize destructive thermal gradients in the ceramic material due to local cooling by air entering the liner through ports for combustion or dilution air, the wa... | 09/21/1976 |
| 3981140 | Gas turbine engine geometry control A single-shaft gas turbine engine suited for road vehicle propulsion has variable inlet and outlet guide vanes in the compressor of the engine and a variable turbine nozzle. These variable features are called engine variable goemetry (EVG). In normal oper... | 09/21/1976 |
| 3977182 | Gas turbine control A fuel and burner variable geometry (BVG) control for a gas turbine engine. Fuel is controlled in response to the product of desired overall fuel-air ratio and a value of air flow derived from gas generator turbine speed. The desired fuel-air ratio is con... | 08/31/1976 |
| 3977186 | Impinging air jet combustion apparatus A combustion liner for a gas turbine combustion apparatus or the like has a head wall and a side wall extending downstream to an outlet for combustion products. A reaction zone is contained within the upstream end of the side wall and a dilution zone down... | 08/31/1976 |
| 3970319 | Seal structure A porous seal element usable as a blade tip seal in a turbomachine or as an element of a labyrinth seal is made up of a large number of strips disposed edgewise to the sealing face of the element and extending in the direction of relative movement of the ... | 07/20/1976 |
| 3970252 | Cooled exhaust duct An exhaust duct for a turbofan aircraft engine includes a bulbous inner cone which blocks direct sight of the turbine through the duct. Ram air from the fan is caught by scoops and conveyed from a plenum into the double outer wall of the exhaust duct and ... | 07/20/1976 |
| 3969892 | Combustion system A combustion system with provisions to minimize undesired exhaust products including carbon monoxide, incompletely burned fuel, and oxides of nitrogen. Air entering the combustion zone of the combustion apparatus is mixed with a relatively large amount of... | 07/20/1976 |
| 3969890 | Helicopter power plant control A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical input... | 07/20/1976 |
| 3964506 | Pressure control system A system for controlling pressure of a fluid, specifically the pressure of servo oil delivered to a clutch which determines the torque transmitted by the clutch. The system includes a pump, a pressure regulating valve to provide servo oil at constant pres... | 06/22/1976 |
| 3963372 | Helicopter power plant control A control system for a helicopter power plant with three power units driving the lifting rotor system. Each power unit comprises a gas-coupled gas turbine engine, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor, ... | 06/15/1976 |
| 3963368 | Turbine cooling A cooling arrangement for high temperature turbines, particularly the first stage nozzles of gas turbine engines. Cooling is effected by compressor discharge air taken from the combustion chamber jacket of the engine. The shrouds of the nozzle have a base... | 06/15/1976 |
| 3958604 | Control valve A hydraulic position servo system includes a primary control valve moved by a mechanical input which embodies a pintle laterally shiftable in a cylinder to differentially throttle two orifices to establish a variable control pressure.... | 05/25/1976 |
| 3958416 | Combustion apparatus A combustion liner for a gas turbine combustion apparatus has a wall of circular cross-section defining a primary air entrance at its upstream end, providing means for introduction of fuel near the upstream end, having a convergent-divergent fuel prevapor... | 05/25/1976 |
| 3958413 | Combustion method and apparatus A combustion method and apparatus for gas turbine engines employs a combustion process and combustion liner structure adapted to promote complete combustion of liquid hydrocarbon fuel and minimize undesired combustion products. Compressed primary air flow... | 05/25/1976 |
| 3953147 | Fluid dynamic machine A fluid dynamic machine has a single rotor providing the rotor portion of a centrifugal compressor and also the rotor portion of an axial-to-radial flow fan. The portion of the rotor blades adjacent the hub define a compressor blading and the axially forw... | 04/27/1976 |
| 3952502 | Gas turbine control A control system for a gas-coupled gas turbine engine particularly directed to control of the setting angle of the power turbine nozzle of the engine and to correlation of the power turbine nozzle setting with fuel supply and with operating parameters of ... | 04/27/1976 |
| 3950114 | Turbine blade A turbine blade having a porous hollow sheet metal airfoil and a base defining a platform, stalk, and root. The airfoil portion is integral with an extension which lies within the blade stalk, the base being cast around this extension. The cast metal lies... | 04/13/1976 |
| 3940153 | Labyrinth seal A labyrinth seal has two relatively rotatable members which are configured to define between them a succession of annular orifice or clearances between seal knives on one member and generally cylindrical surfaces or lands on the other. The members define ... | 02/24/1976 |
| 3938324 | Premix combustor with flow constricting baffle between combustion and dilution zones A combustion liner for a gas turbine combustion apparatus has a wall of circular cross-section defining a primary air entrance at its upstream end, providing means for introduction of fuel near the upstream end, having a convergent-divergent fuel prevapor... | 02/17/1976 |
| 3938321 | Gas turbine control A control system for a gas-coupled gas turbine engine particularly directed to control of the setting angle of the power turbine nozzle of the engine and to correlation of the power turbine nozzle setting with fuel supply and with operating parameters of ... | 02/17/1976 |
| 3938320 | Starting system for a helicopter power plant control A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical input... | 02/17/1976 |
| 3937013 | By-pass jet engine with centrifugal flow compressor A simple by-pass type jet propulsion engine includes a centrifugal compressor and a centripetal turbine mounted back-to-back and a combustion apparatus disposed radially outwardly of the turbine. These constitute the core engine; the fan part of the engin... | 02/10/1976 |
| 3936223 | Compressor diffuser A diffuser for a radial-flow compressor with a circumferentially and radially extending annular splitter plate dividing the entrance portion of each diffusing passage into two parallel passages.... | 02/03/1976 |
| 3934408 | Ceramic combustion liner A combustion liner for a gas turbine combustion apparatus has a wall of ceramic material. To minimize destructive thermal gradients in the ceramic material due to local cooling by air entering the liner through ports for combustion or dilution air, the wa... | 01/27/1976 |
| 3933442 | Laminated body A porous seal element usable as a blade tip seal in a turbomachine or as an element of a labyrinth seal is made up of a large number of strips disposed edgewise to the sealing face of the element and extending in the direction of relative movement of the ... | 01/20/1976 |
| 3930368 | Combustion liner air valve A combustion liner suitable for an automotive gas turbine has variable primary and secondary air admission ports through the wall of the liner. The areas of these sets of ports are varied jointly by two annular valve sleeve assemblies reciprocable on the ... | 01/06/1976 |
| 3930369 | Lean prechamber outflow combustor with two sets of primary air entrances A combustion apparatus for gas turbine engines particularly adapted to reduce emissions to meet automotive requirements. The fuel is laid on the wall of a cylindrical prechamber and evaporated from the wall by combustion air which is introduced through a ... | 01/06/1976 |
