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U.S. Patent Specifications

U.S. Patent Specifications 2,657,884. Fuel Cell. James A. Merrill, Ohio, assignor to Wingfoot Corporation, Ohio. Application November 9, 1950. A fuel cell for installation in a chamber in a plane which is enclosed by rigid walls includi feners, said fuel cell comprising liquid-tight en These details and drawings of patents granted in the United States are taken, by permission of the Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, Southampton Buildings, Chancery Lane, London, W.C.2. 2,654,215. Turbine Power Plant Having Auxiliary 2,655,326. Gust-Alleviating Flap System for Air­ Air Inlet and Thrust Augmcntcr. Ransom S. Thomp­ craft. Fred E. Weick, Calvert Hills, Md., assignor to son, Middle Haddam, Conn., assignor to United Air­ Engineering and Research Corporation, Riverdale, craft Corporation, East Hartford, Conn. Application Md. Application December 4, 1947. walls of a flexible sheet material which con September 27, 1949. A system for counteracting the effect of gusts on exactly to the internal outlines of the chamber, the wing of an aircraft to reduce vertical acceleration flexible walls having depressions formed therei of the wing due to such gusts, comprising a flap defined by the stifleners and enclosure walls o pivoted adjacent the trailing edge of the wing having chamber; an outlet in the cell; and a plurality c a normal position in which it forms part of the aero­ flatablc members disposed internally of the cell foil contour of the wing, a reversible electric motor for confined in said depressions formed in the cell, selectively moving the flap about its pivot axis to members operating upon inflation to fill these positions above and below its normal position to prcssions substantially completely,.preventing po vary the lift of the wing, a mass suspended with re­ ing of the liquid and insuring complete drainage o spect to the wing for relative vertical movement from cell through the outlet. a normal position upward or downwardly with re­ spect to the wing upon sudden vertical acceleration In a jet propulsion unit for an aeroplane, a jet of the wing, means operable by relative movement of 2,658,330. Liquid Fuel Supply System for Intel engine having an air intake forming a part thereof the mass with respect to the wing in one direction to Combustion Turbines with Afterburners. Frede and a compressor receiving air from said inlet, a cause the motor to rotate in a direction to move the Henry Carey, Cheltenham, England, assignor cowling surrounding said engine and forming a ram flap upwardly away from its normal position within Dowty Equipment Limited, Cheltenham, Engl air duct forward thereof and providing a path con­ ducting air to said intake, means for providing a Application November 2, 1948. second path of unrestricted airflow from outside said In combination with a main burner of the cowling into said air intake at low forward speeds of type and an exhaust reheating burner of the di the aeroplane including mechanism for axially injection type, of an aircraft internal combust separating said cowling and exposing said intake to turbine engine, a fuel source, a circulating pum the free airstrcam, an exhaust conduit for the engine, first conduit means for circulating fuel normally i and co-operating mechanism carried by said cowling closed circuit which includes said main burner and the engine forming an ejector to withdraw air said circulating pump, a supply pump, norm from the airstream and augment the stream issuing connected to said first conduit means to aug from said exhaust conduit. the aerofoil contour of the wing and operable by relative movement of the mass in the opposite direc­ 2,654,993. Gas Turbine Engine with Multiple tion to rotate the motor in its opposite direction to Turbines. Frank Morgan Owner, Bristol, England, move the flap downwardly, and means operable by assignor to The Bristol Aeroplane Company Limited, movement of the mass to its normal position from a Bristol, England. Application September 16, 1949. In position away therefrom and while the flap is de­ Great Britain September 27, 1948. flected from its normal position for reversing the direction of rotation of the motor to move the flap toward its normal position and operable upon move­ ment of the flap to its normal position to dc-encrgize the motor whereby movement of the flap is stopped. 2,657,532. Liquid Fuel Atomizer Located Upstream of a Flame Stabilizing Battle. John Rcid, Elstead, and Allan G. Earl, Cambcrlcy, England, assignors to Power Jets (Research and Development) Limited, London, England. Application August 23, 1949. Claim priority, application Great Britain Septem­ ber 2, 1948. Combustion apparatus for burning liquid fuel in a fast-moving gas stream including a duct for carrying said stream, a fuel atomizing system in the duct, said supply to the main burner, a second conduit mean system comprising at least one liquid fuel injector for delivering fuel abnormally from the supply pum directed along the duct and means to provide a re­ to the main burner by way in part of the first condu sisting medium facing and close to said injector so means, and from the circulating pump to the re that fuel issuing from the injector is caused to spread heating burner, also by way in part of the first condu out across and mix with the stream, flame stabilizing means, a change-over valve arranged in common i baffle means in the duct adjacent to, downstream of and including elements controlling each of the tw and aligned with the atomizing system, said baffle conduit means, and shiftable from a normal positio means defining a stabilized combustion zone, and an wherein the two pumps co-operate to supply fuel t A gas turbine power plant comprising at least two igniter within said zone. the main burner, and fuel supply to the reheating turbine engines each of which comprises a compressor, combustion equipment which receives air from the burner is cut off, to an abnormal position wherein the compressor and in which fuel is burnt, and a main pumps are isolated, and supply the one the main turbine which receives the gases from the combustion burner and the other the reheating burner, a throttle equipment and comprising a pair of independently- lever shiftable through a normal range and also there- rotating rotors one of which is adapted to drive the beyond in the throttle-opening sense through an compressor, said rotors being opcrativcly associated abnormal range, means including said throttle lever in series with the compressor rotor positioned up­ for regulating supply of fuel from the supply pump, stream of the other of said rotors so that the gases and operable automatically upon movement of the from the combustion equipment pass first through throttle lever into its abnormal range to shift the the compressor rotor and then through said other changeover valve into its abnormal position, and an aneroid-controlled release valve in the second conduit1 rotor, an auxiliary turbine mechanically independent means, and a co-operating pressure-controlled by­ of said turbine engines, and means for withdrawing pass valve, to regulate supply to the reheating burner, gases from said turbine engines at a point between the rotors thereof and supplying the gases to said during abnormal operation, automatically in accord­ auxiliary turbine. ance with pressure altitude. Aircraft Engineering http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology , Volume 26 (3): 1 – Mar 1, 1954
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032408
Publisher site
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Abstract

2,657,884. Fuel Cell. James A. Merrill, Ohio, assignor to Wingfoot Corporation, Ohio. Application November 9, 1950. A fuel cell for installation in a chamber in a plane which is enclosed by rigid walls includi feners, said fuel cell comprising liquid-tight en These details and drawings of patents granted in the United States are taken, by permission of the Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, Southampton Buildings, Chancery Lane, London, W.C.2. 2,654,215. Turbine Power Plant Having Auxiliary 2,655,326. Gust-Alleviating Flap System for Air­ Air Inlet and Thrust Augmcntcr. Ransom S. Thomp­ craft. Fred E. Weick, Calvert Hills, Md., assignor to son, Middle Haddam, Conn., assignor to United Air­ Engineering and Research Corporation, Riverdale, craft Corporation, East Hartford, Conn. Application Md. Application December 4, 1947. walls of a flexible sheet material which con September 27, 1949. A system for counteracting the effect of gusts on exactly to the internal outlines of the chamber, the wing of an aircraft to reduce vertical acceleration flexible walls having depressions formed therei of the wing due to such gusts, comprising a flap defined by the stifleners and enclosure walls o pivoted adjacent the trailing edge of the wing having chamber; an outlet in the cell; and a plurality c a normal position in which it forms part of the aero­ flatablc members disposed internally of the cell foil contour of the wing, a reversible electric motor for confined in said depressions formed in the cell, selectively moving the flap about its pivot axis to members operating upon inflation to fill these positions above and below its normal position to prcssions substantially completely,.preventing po vary the lift of the wing, a mass suspended with re­ ing of the liquid and insuring complete drainage o spect to the wing for relative vertical movement from cell through the outlet. a normal position upward or downwardly with re­ spect to the wing upon sudden vertical acceleration In a jet propulsion unit for an aeroplane, a jet of the wing, means operable by relative movement of 2,658,330. Liquid Fuel Supply System for Intel engine having an air intake forming a part thereof the mass with respect to the wing in one direction to Combustion Turbines with Afterburners. Frede and a compressor receiving air from said inlet, a cause the motor to rotate in a direction to move the Henry Carey, Cheltenham, England, assignor cowling surrounding said engine and forming a ram flap upwardly away from its normal position within Dowty Equipment Limited, Cheltenham, Engl air duct forward thereof and providing a path con­ ducting air to said intake, means for providing a Application November 2, 1948. second path of unrestricted airflow from outside said In combination with a main burner of the cowling into said air intake at low forward speeds of type and an exhaust reheating burner of the di the aeroplane including mechanism for axially injection type, of an aircraft internal combust separating said cowling and exposing said intake to turbine engine, a fuel source, a circulating pum the free airstrcam, an exhaust conduit for the engine, first conduit means for circulating fuel normally i and co-operating mechanism carried by said cowling closed circuit which includes said main burner and the engine forming an ejector to withdraw air said circulating pump, a supply pump, norm from the airstream and augment the stream issuing connected to said first conduit means to aug from said exhaust conduit. the aerofoil contour of the wing and operable by relative movement of the mass in the opposite direc­ 2,654,993. Gas Turbine Engine with Multiple tion to rotate the motor in its opposite direction to Turbines. Frank Morgan Owner, Bristol, England, move the flap downwardly, and means operable by assignor to The Bristol Aeroplane Company Limited, movement of the mass to its normal position from a Bristol, England. Application September 16, 1949. In position away therefrom and while the flap is de­ Great Britain September 27, 1948. flected from its normal position for reversing the direction of rotation of the motor to move the flap toward its normal position and operable upon move­ ment of the flap to its normal position to dc-encrgize the motor whereby movement of the flap is stopped. 2,657,532. Liquid Fuel Atomizer Located Upstream of a Flame Stabilizing Battle. John Rcid, Elstead, and Allan G. Earl, Cambcrlcy, England, assignors to Power Jets (Research and Development) Limited, London, England. Application August 23, 1949. Claim priority, application Great Britain Septem­ ber 2, 1948. Combustion apparatus for burning liquid fuel in a fast-moving gas stream including a duct for carrying said stream, a fuel atomizing system in the duct, said supply to the main burner, a second conduit mean system comprising at least one liquid fuel injector for delivering fuel abnormally from the supply pum directed along the duct and means to provide a re­ to the main burner by way in part of the first condu sisting medium facing and close to said injector so means, and from the circulating pump to the re that fuel issuing from the injector is caused to spread heating burner, also by way in part of the first condu out across and mix with the stream, flame stabilizing means, a change-over valve arranged in common i baffle means in the duct adjacent to, downstream of and including elements controlling each of the tw and aligned with the atomizing system, said baffle conduit means, and shiftable from a normal positio means defining a stabilized combustion zone, and an wherein the two pumps co-operate to supply fuel t A gas turbine power plant comprising at least two igniter within said zone. the main burner, and fuel supply to the reheating turbine engines each of which comprises a compressor, combustion equipment which receives air from the burner is cut off, to an abnormal position wherein the compressor and in which fuel is burnt, and a main pumps are isolated, and supply the one the main turbine which receives the gases from the combustion burner and the other the reheating burner, a throttle equipment and comprising a pair of independently- lever shiftable through a normal range and also there- rotating rotors one of which is adapted to drive the beyond in the throttle-opening sense through an compressor, said rotors being opcrativcly associated abnormal range, means including said throttle lever in series with the compressor rotor positioned up­ for regulating supply of fuel from the supply pump, stream of the other of said rotors so that the gases and operable automatically upon movement of the from the combustion equipment pass first through throttle lever into its abnormal range to shift the the compressor rotor and then through said other changeover valve into its abnormal position, and an aneroid-controlled release valve in the second conduit1 rotor, an auxiliary turbine mechanically independent means, and a co-operating pressure-controlled by­ of said turbine engines, and means for withdrawing pass valve, to regulate supply to the reheating burner, gases from said turbine engines at a point between the rotors thereof and supplying the gases to said during abnormal operation, automatically in accord­ auxiliary turbine. ance with pressure altitude. Aircraft Engineering

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Mar 1, 1954

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