US2514248A - Device for automatically adjusting a variable jet nozzle for a jet propulsion unit with variations in the temperature prevailing in the jet pipe - Google Patents

Device for automatically adjusting a variable jet nozzle for a jet propulsion unit with variations in the temperature prevailing in the jet pipe Download PDF

Info

Publication number
US2514248A
US2514248A US739184A US73918447A US2514248A US 2514248 A US2514248 A US 2514248A US 739184 A US739184 A US 739184A US 73918447 A US73918447 A US 73918447A US 2514248 A US2514248 A US 2514248A
Authority
US
United States
Prior art keywords
jet
pipe
ram
nozzle
temperature
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US739184A
Inventor
Lombard Adrian Albert
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to GB2514248X priority Critical
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US2514248A publication Critical patent/US2514248A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06Varying effective area of jet pipe or nozzle
    • F02K1/15Control or regulation

Description

July 4, 1950 A. A. LOMBARD ET AL 2,514,243
DEVICE FOR AUTOMATICALLY ADJUSTING A VARIABLE JET NOZZLE FOR A JET PROPULSION UNIT WITH VARIATIONS IN THE TEMPERATURE PREVAILING IN THE JET PIPE Filed April 3, 1947 2 Sheets-Sheet 1 INVENTORS A. A. LOMBARD M.V. GOU KLAY 4' 6. SKIPWIT July 4, 1950 A. A. LOMBARD ET AL 2,514,243
DEVICE FOR AUTOMATICALLY ADJUSTING A VARIABLE JET NOZZLE FOR A JET PROPULSION UNIT WITH VARIATIONS IN THE TEMPERATURE PREVAILING IN THE JET PIPE Filed April 3, 1947 2 Sheets-Sheet 2 al a/5? Zomlard (M V gouff Patented July 4, 1950 DEVICE FOR AUTOMATICALLY ADJUSTING A VARIABLE JET NOZZLE FOR A JET PRO- PULSION UNIT WITH VARIATIONS IN THE TEMPERATURE PIPE PREVAILING IN THE JET Adrian Albert Lombard, Clitheroe, England, and Gordon Kenneth Luker Gourlay, deceased, late of Skipton, Yorkshire, England, by'Margaret Virginia Grimwood, .Cranleigh, and Grey Skipwith, Mortimer, England, administrators, assignors to Rolls-Royce Limited, Derby, England, a company of Great Britain Application April 3, 1947, Serial No. 139,184 In Great Britain March 9, 1945 Section 1, Public Law 690, August 8, 1946 Patent expires March 9, 1965 3 Claims. (Cl. 60-455) This invention relates to variable jet nozzles for jet propulsion units and has for its object to provide an improved construction of automatic control means whereby the area of the nozzle may be controlled in accordance with the temperature of the gas in the jet-pipe.
According to this invention the parts which are movable to adjust the area of the nozzle are operated by a hydraulic ram which is itself controlled by a. temperature-sensitive device in the Jet-pipe.
Preferably the supply of pressure fluid to the hydraulic ram is controlled by a valve and there is provided a follow-up device actuated by the ram to cut oil the supply of said pressure fluid.
Specific embodiments of the present invention will now be described by way of example with reference to the accompanying drawing whereof,
Figure 1 is a diagrammatic view of an automatic control means for a variable jet nozzle in accordance with the present invention.
Figure la is a fragmentary longitudinal section of the tail end oi the jet pipe showing the details of the nozzle and the temperature responsive device, and
Figure 2 is a diagrammatic view of a modified construction of such control means.
Referring to Figure l, the jet-pipe is generally indicated by the reference numeral 5, the rear end of said pipe being provided with a pair of sector members i which are adjustable about a common pivot point 1 so as to vary the discharge area of the nozzle. The sector members I are connected by a linkage 8 with a hydraulic ram generally indicated at 9 the arrangement being that when pressure fluid is admitted to one end of the ram the sector members will be adjusted in one sense and when pressure fluid is admitted to the other end of the ram the sector members will be adjusted in the opposite sense. Such a general arrangement of power control has been described in the specification to patent agflication Serial No. 693,444, flled August 28, 1 8.
Pressure fluid is supplied to the hydraulic ram 9 by a pump It the suction side of which is connected with a reservoir II to which the fluid exhausted from the system is returned by a pipe II. The supply of fluid under pressure to, and the drain of fluid from, the ram 9 to effect its operation is controlled by a valve means indisure fluid to be delivered from the pump It to the ram 9 to adjust the sector members 6. The movement of the ram 9 is imparted thereby to the follow-up sleeve ll so that the latter cuts of! the supply of pressure fluid to the ram and at the same time closes the drain from the opposite end of the ram piston to the reservoir H by pipe l2. It will be appreciated that the end of the hydraulic ram 9 which is supplied with pressure fluid or drained of fluid is governed by the direction of movement of the piston I from its closed position such movement being determined by the temperature-sensitive device It in the jet pipe.
In use, if it is assumed that the piston I4 is moved by the temperature-sensitive device It to the right, pressure fluid passes from pump III by pipe ill to the left hand side of the hydraulic ram and simultaneously pipe 29 which connects with the right hand side of the ram is connected to drain by means of pipe 2|. The passage of fluid from pump Hi to pipe I9 and from pipe 29 to pipe 2| i stopped when the sleeve ll, which is moved to the right by the ram piston, closes the ports associated with said pipes. Similarly when the piston is moved to the left pressure fluid passes from pump ill to the right hand side of the hydraulic ram 9 by way of pipe 20 and the drain from the hydraulic ram is eflected by pipe l9 which i placed in communication with pipe ii. The movement of the rampiston will continue until the sleeve I! has been moved to close the ports associated with said pipes.
It will be observed from the flgure that a spring .22 is disposed between one end of the piston ll andthe adjacent end of the sleeve ll so as to maintain the piston H in engagement with the lever II.
In the modified construction shown in Figure 2 instead of operating the piston valve ll of the valve means 13 directly through a mechanical linkage by the temperature-sensitive device l6,
it is operated by fluid pressure which is derived from the same source (that is the pump M) as that which supplies the ram 9.
As in the construction described with reference to Figure 1 the piston valve I4 is engaged by a spring 22 so that it is urged in one direction and said piston valve is so mounted in the followup sleeve ll as to constitute a piston therein to which fluid under pressure may be supplied to move the valve towards the right or in which fluid is connected to drain so that the piston I4 is urged by spring 22 towards the left.
The temperature-sensitive device 16 is arranged to operate the piston 23 of a valve 24 which regulates the passage of fluid to, and from, the left hand end of the piston ll. The piston 23 is maintained in contact with the temperature-sensitive device by a. spring 25. With this arrangement if the piston 23 is moved towards the right, pressure fluid from the pump I is delivered to valve 24 by pipe 28 and passes by pipe 2'! to the piston I I. As a consequence pressure fluid is admitted to the left hand side of the ram 9 as described with reference to Figure 1 and such supply is terminated when the piston of hydraulic ram 9 has moved the sleeve I! towards the right to close the ports of valve means I. Similarly if the piston 23 is moved by spring 25 towards the left, the left hand side of piston I4 is connected with the reservoir H by means of pipes 21, 29 and piston II is therefore moved towards the left by spring 22. When this occurs pressure fluid will pass from the pump it to the right hand side of hydraulic ram 9 by pipe 20 such supply being stopped when the sleeve H has been moved to a predetermined extent towards the left.
It will be appreciated therefore that in the two constructions described the adjustment of the nozzle area to maintain constant temperature in the jet-pipe is determined by the temperature-sensitive device It disposed within the jet-pipe.
The particular advantage of the construction described with reference to Figure 2 is that the efiort required to be exerted by the temperaturesensitive device 16 can be made substantially less than that required to operate the piston I4 directly. The advantage of using a follow-up system of control as in the two constructions described is that hunting is avoided in the adjustment of the area of the nozzle.
We claim:
1. An aircraft jet propulsion system comprising in combination a jet pipe having an exit propelling nozzle, parts movable to adjust the area of said nozzle; a hydraulic ram to move said parts; a hydraulic pump to supply pressure liquid to said ram, a temperature sensitive device in said jet pipe, a first valve part actuated by said temperature sensitive device, a second valve part actuated by said ram, said valve parts being arranged in juxtaposition, so that supply of pressure liquid to the ram is initiated by movement of the first part and is cut oil by the resultant movement of the second part in follow-up action, and so that an increase in the temperature sensed by said temperature sensitive device results in movement of the parts to increase the area of said nozzle and vice-versa.
2. An aircraft jet propulsion system comprising in combination a jet pipe having an exit propelling nozzle, parts movable to adjust the area of said nozzle, a hydraulic ram to move said parts, a hydraulic pump to supply pressure liquid to said ram, a temperature sensitive device in said jet pipe, a part associated with said temperature sensitive device and moved in accordance with the sensed temperature, a first valve part, a mechanical connection between said part moved in accordance with sensed temperature and said first valve part, a second valve part actuated by said ram, said valve parts being arranged in juxtaposition so that supply of pressure liquid to the ram is initiated by movement of the first valve part and is cut off by the resultant movement ofthe second valve part in follow-up action, and so that an increase of sensed temperature results in movement of the parts to increase the nozzle area and vice-versa.
3. An aircraft jet propulsion system comprising in combination, a jet pipe having an exit propelling nozzle, parts movable to adjust the area of said nozzle, a hydraulic ram to move said parts, a hydraulic pump to supply pressure liquid to said ram, a temperature sensitive device in said jet pipe, a part associated with said temperature sensitive device and moved in accordance with the sensed temperature, a servo valve part, a mechanical connection between said servo valve part and said part moved in accordance with sensed temperature, a first control valve part actuated by hydraulic pressure controlled by said servo valve, so that said first control valve part follows the movement of the part moved in accordance with sensed temperature, a second control valve part actuated by said ram, said control valve parts being arranged in juxtaposition so that supply of pressure liquid to the ram is initiated by movement of the first control part and is cut off by the resultant movement of the second control valve part in followup action, and so that an increase of sensed temperature results in movement of the parts to increase the nozzle area and vice-versa.
ADRIAN ALBERT LOMBARD. By MARGARET VIRGINIA GRIMWOOD. GREY SKIPWITH, Administrators of the Estate of Gordon Kenneth Luker Gourlay, Deceased.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date.
2,095,991 Lysholm Oct. 19, 1937 2,338,021 Bennett Dec. 28, 1943 2,363,179 Harrington et a1. Nov. 21, 944 2,372,686 Sedille Apr. 3, 1945 2,392,622 Traupel Jan. 8, 1946 2,402,363 Bradbury June 18, 1946 2,411,895 Poole 1 Dec. 3, 1946
US739184A 1945-03-09 1947-04-03 Device for automatically adjusting a variable jet nozzle for a jet propulsion unit with variations in the temperature prevailing in the jet pipe Expired - Lifetime US2514248A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2514248X 1945-03-09

Publications (1)

Publication Number Publication Date
US2514248A true US2514248A (en) 1950-07-04

Family

ID=10908856

Family Applications (1)

Application Number Title Priority Date Filing Date
US739184A Expired - Lifetime US2514248A (en) 1945-03-09 1947-04-03 Device for automatically adjusting a variable jet nozzle for a jet propulsion unit with variations in the temperature prevailing in the jet pipe

Country Status (1)

Country Link
US (1) US2514248A (en)

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2635419A (en) * 1948-09-30 1953-04-21 Curtiss Wright Corp Adjustable discharge nozzle for jet engines
US2677233A (en) * 1949-06-30 1954-05-04 United Aircraft Corp Exhaust nozzle switch responsive to afterburner pressure ratio
US2683348A (en) * 1950-05-26 1954-07-13 Honeywell Regulator Co Modulated continuous flow hydraulic control apparatus
US2683347A (en) * 1950-01-09 1954-07-13 Honeywell Regulator Co Hydraulic control apparatus
US2688841A (en) * 1947-02-06 1954-09-14 Hermann Oestrich Control device for gas turbine propulsion plants
US2699037A (en) * 1951-06-18 1955-01-11 Rolls Royce Gas-turbine engine with reheat combustion equipment and variable area nozzle
US2699646A (en) * 1949-06-30 1955-01-18 Gen Electric Gas turbine power plant having variable exhaust area and control system therefor
US2701440A (en) * 1948-04-19 1955-02-08 Mcdonnell Aircraft Corp Actuator for variable inlet cowl for pulse jets
US2705864A (en) * 1951-06-06 1955-04-12 Bendix Aviat Corp Electronic control for gas turbine engines
US2706383A (en) * 1949-12-15 1955-04-19 Gen Electric Control for gas turbine power plant
US2706886A (en) * 1950-06-14 1955-04-26 Honeywell Regulator Co Coordinated hydraulic control apparatus
US2736166A (en) * 1956-02-28 Afterburning and exhaust nozzle
US2737016A (en) * 1950-09-15 1956-03-06 Solar Aircraft Co Afterburner controls
US2737775A (en) * 1950-09-15 1956-03-13 Solar Aircraft Co Afterburner electric controls
US2738644A (en) * 1950-04-15 1956-03-20 Gen Electric Surge control for axial flow compressors
US2739441A (en) * 1949-11-23 1956-03-27 Gen Electric Temperature responsive control system for gas turbine power plant having exhaust reheating
US2761517A (en) * 1952-05-15 1956-09-04 Gen Motors Corp Control mechanism for propellers of the contrarotation type
US2774215A (en) * 1949-04-22 1956-12-18 Bendix Aviat Corp Tailpipe or afterburning control for turbojet engines
US2776536A (en) * 1950-08-19 1957-01-08 Honeywell Regulator Co Combustion engine control apparatus
US2778190A (en) * 1950-06-08 1957-01-22 Republic Aviat Corp Variable area nozzle for jet engines
US2790303A (en) * 1950-01-28 1957-04-30 Honeywell Regulator Co Jet engine fuel and nozzle area control apparatus
US2791882A (en) * 1950-09-29 1957-05-14 Westinghouse Electric Corp Variable area nozzle for jet propulsion engine
US2793491A (en) * 1950-12-07 1957-05-28 Gen Motors Corp Variable area jet nozzle
US2934888A (en) * 1953-01-15 1960-05-03 Honeywell Regulator Co Gas turbine combustion engine control apparatus for controlling the exhaust area and fuel flow
US2960155A (en) * 1953-05-26 1960-11-15 Bendix Corp Afterburner fuel metering control
US3005308A (en) * 1952-08-25 1961-10-24 Bader Frank Variable area nozzle arrangement
US3021668A (en) * 1957-01-11 1962-02-20 Bendix Corp Nozzle area control for turbojet engines
US3038305A (en) * 1953-01-23 1962-06-12 Lockheed Aircraft Corp Subsonic, supersonic propulsive nozzle
US3060686A (en) * 1956-06-15 1962-10-30 Garrett Corp Augmented gas turbine engine and controls
US3285623A (en) * 1964-09-08 1966-11-15 Daimler Benz Ag Anti-tilting system for vehicles
US20040068977A1 (en) * 2002-09-12 2004-04-15 Mckay Richard John Thrust reverser for a jet engine and hydraulic actuator
US20050062378A1 (en) * 2002-03-22 2005-03-24 Frank Wojcik Memory storage device having a locking handle

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2095991A (en) * 1933-03-08 1937-10-19 Milo Ab Gas turbine system of the continuous combustion type
US2338021A (en) * 1940-02-10 1943-12-28 Bennett Roland Pressure controlled system
US2363179A (en) * 1942-02-21 1944-11-21 Vickers Inc Power transmission
US2372686A (en) * 1941-03-10 1945-04-03 Sedille Marcel Henri Louis System and device for controlling thermal gas turbine motive units
US2392622A (en) * 1942-04-18 1946-01-08 Sulzer Ag Gas turbine plant
US2402363A (en) * 1943-10-21 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2411895A (en) * 1944-04-15 1946-12-03 United Aircraft Corp Nozzle control

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2095991A (en) * 1933-03-08 1937-10-19 Milo Ab Gas turbine system of the continuous combustion type
US2338021A (en) * 1940-02-10 1943-12-28 Bennett Roland Pressure controlled system
US2372686A (en) * 1941-03-10 1945-04-03 Sedille Marcel Henri Louis System and device for controlling thermal gas turbine motive units
US2363179A (en) * 1942-02-21 1944-11-21 Vickers Inc Power transmission
US2392622A (en) * 1942-04-18 1946-01-08 Sulzer Ag Gas turbine plant
US2402363A (en) * 1943-10-21 1946-06-18 Westinghouse Electric Corp Turbine apparatus
US2411895A (en) * 1944-04-15 1946-12-03 United Aircraft Corp Nozzle control

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2736166A (en) * 1956-02-28 Afterburning and exhaust nozzle
US2688841A (en) * 1947-02-06 1954-09-14 Hermann Oestrich Control device for gas turbine propulsion plants
US2701440A (en) * 1948-04-19 1955-02-08 Mcdonnell Aircraft Corp Actuator for variable inlet cowl for pulse jets
US2635419A (en) * 1948-09-30 1953-04-21 Curtiss Wright Corp Adjustable discharge nozzle for jet engines
US2774215A (en) * 1949-04-22 1956-12-18 Bendix Aviat Corp Tailpipe or afterburning control for turbojet engines
US2699646A (en) * 1949-06-30 1955-01-18 Gen Electric Gas turbine power plant having variable exhaust area and control system therefor
US2677233A (en) * 1949-06-30 1954-05-04 United Aircraft Corp Exhaust nozzle switch responsive to afterburner pressure ratio
US2739441A (en) * 1949-11-23 1956-03-27 Gen Electric Temperature responsive control system for gas turbine power plant having exhaust reheating
US2706383A (en) * 1949-12-15 1955-04-19 Gen Electric Control for gas turbine power plant
US2683347A (en) * 1950-01-09 1954-07-13 Honeywell Regulator Co Hydraulic control apparatus
US2790303A (en) * 1950-01-28 1957-04-30 Honeywell Regulator Co Jet engine fuel and nozzle area control apparatus
US2738644A (en) * 1950-04-15 1956-03-20 Gen Electric Surge control for axial flow compressors
US2683348A (en) * 1950-05-26 1954-07-13 Honeywell Regulator Co Modulated continuous flow hydraulic control apparatus
US2778190A (en) * 1950-06-08 1957-01-22 Republic Aviat Corp Variable area nozzle for jet engines
US2706886A (en) * 1950-06-14 1955-04-26 Honeywell Regulator Co Coordinated hydraulic control apparatus
US2776536A (en) * 1950-08-19 1957-01-08 Honeywell Regulator Co Combustion engine control apparatus
US2737016A (en) * 1950-09-15 1956-03-06 Solar Aircraft Co Afterburner controls
US2737775A (en) * 1950-09-15 1956-03-13 Solar Aircraft Co Afterburner electric controls
US2791882A (en) * 1950-09-29 1957-05-14 Westinghouse Electric Corp Variable area nozzle for jet propulsion engine
US2793491A (en) * 1950-12-07 1957-05-28 Gen Motors Corp Variable area jet nozzle
US2705864A (en) * 1951-06-06 1955-04-12 Bendix Aviat Corp Electronic control for gas turbine engines
US2699037A (en) * 1951-06-18 1955-01-11 Rolls Royce Gas-turbine engine with reheat combustion equipment and variable area nozzle
US2761517A (en) * 1952-05-15 1956-09-04 Gen Motors Corp Control mechanism for propellers of the contrarotation type
US3005308A (en) * 1952-08-25 1961-10-24 Bader Frank Variable area nozzle arrangement
US2934888A (en) * 1953-01-15 1960-05-03 Honeywell Regulator Co Gas turbine combustion engine control apparatus for controlling the exhaust area and fuel flow
US3038305A (en) * 1953-01-23 1962-06-12 Lockheed Aircraft Corp Subsonic, supersonic propulsive nozzle
US2960155A (en) * 1953-05-26 1960-11-15 Bendix Corp Afterburner fuel metering control
US3060686A (en) * 1956-06-15 1962-10-30 Garrett Corp Augmented gas turbine engine and controls
US3021668A (en) * 1957-01-11 1962-02-20 Bendix Corp Nozzle area control for turbojet engines
US3285623A (en) * 1964-09-08 1966-11-15 Daimler Benz Ag Anti-tilting system for vehicles
US20050062378A1 (en) * 2002-03-22 2005-03-24 Frank Wojcik Memory storage device having a locking handle
US20040068977A1 (en) * 2002-09-12 2004-04-15 Mckay Richard John Thrust reverser for a jet engine and hydraulic actuator

Similar Documents

Publication Publication Date Title
US2716946A (en) Hydraulic control system
US2931168A (en) Variable stator engine control system
US2487618A (en) Hydraulic steering powke
US2411895A (en) Nozzle control
US3047257A (en) Device for changing airfoil profile
US3521535A (en) Time modulated pneumatically actuated position control mechanism
US2238061A (en) Fluid pressure system and control therefor
US2706520A (en) Fluid distributing apparatus
US3285262A (en) Aerodynamic or hydrodynamic servovalve, especially for use for the guidance and stabilisation of rockets
US2532960A (en) Brake booster
SU776574A3 (en) Valve switch
US2905191A (en) Valve
US2503048A (en) Means for controlling the flow of liquid fuel to prime movers
GB920662A (en) A valve device for controlling the fluid pressure differential across an orifice in a fluid conduit
GB1010502A (en) Adjustable, metered, directional flow control arrangement
US3223103A (en) Regulating device including a distributor having double-acting knife-edges
US2484603A (en) Hydraulic control device
US2385351A (en) Control system for hydraulically actuated devices
US2328979A (en) Power transmission
US2989950A (en) Pneumatic control device
US3091080A (en) Control system for afterburning gas turbine engine
US3295420A (en) Hydraulic actuator
GB1092406A (en) Evacuating valve assembly for a hydraulic jack
US2219488A (en) Liquid pressure remote control system
US3031842A (en) Thrust control for solid rocket