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GB759787A - Improvements in pressure sensitive devices - Google Patents

Improvements in pressure sensitive devices

Info

Publication number
GB759787A
GB759787A GB697354A GB697354A GB759787A GB 759787 A GB759787 A GB 759787A GB 697354 A GB697354 A GB 697354A GB 697354 A GB697354 A GB 697354A GB 759787 A GB759787 A GB 759787A
Authority
GB
United Kingdom
Prior art keywords
pressure
passage
ram
lever
fuel ratio
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
Application number
GB697354A
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.)
Hobson Ltd H M
HM Hobson Ltd
Original Assignee
Hobson Ltd H M
HM Hobson Ltd
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
Application filed by Hobson Ltd H M, HM Hobson Ltd filed Critical Hobson Ltd H M
Priority to GB697354A priority Critical patent/GB759787A/en
Publication of GB759787A publication Critical patent/GB759787A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Supercharger (AREA)

Abstract

759,787. Gas turbine plant; jet propulsion 'engines. HOBSON, Ltd., H. M., and GRENLAND, L. S. Dec. 3, 1954 [March 10, 1954], No. 6973/54. Class 110(3) [Also in Group XXIX] A Mach number control unit for reducing the value of a signal pressure applied to an air-fuel ratio controller of a combustion turbine or ram jet engine upon the attainment by an airborne vehicle propelled by the turbine or engine of a predetermined Mach number, as in Specification 729,077, comprises a pressure responsive diaphragm 10 subject on its right-hand face to static pressure and rigidly connected to a lever 11 pivoted at 12 and to an evacuated, pressure responsive element 9. The signal pressure applied to the air-fuel ratio controller is ram pressure which is transmitted through a passage 6 having a restriction 4 on the downstream side of which is a static pressure vent 3, 8 normally closed by a valve 7 which is actuated by the lever 11. A passage containing an adjustable restriction 19 leads from the passage 6 to the chamber containing the element 9 and this chamber has a restricted outlet 2 so that the pressure that acts in the valveopening direction on the difference of areas of the diaphragm 10 and element 9 is an adjustable fraction of ram pressure. Specification 740,510 [Group XXXIII], also is referred to.
GB697354A 1954-03-10 1954-03-10 Improvements in pressure sensitive devices Expired GB759787A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB697354A GB759787A (en) 1954-03-10 1954-03-10 Improvements in pressure sensitive devices

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB697354A GB759787A (en) 1954-03-10 1954-03-10 Improvements in pressure sensitive devices

Publications (1)

Publication Number Publication Date
GB759787A true GB759787A (en) 1956-10-24

Family

ID=9824221

Family Applications (1)

Application Number Title Priority Date Filing Date
GB697354A Expired GB759787A (en) 1954-03-10 1954-03-10 Improvements in pressure sensitive devices

Country Status (1)

Country Link
GB (1) GB759787A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2356001A1 (en) * 1976-06-24 1978-01-20 Rolls Royce FUEL CIRCUIT CONTROL SYSTEM FOR AIRPLANE TURBOREACTOR

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2356001A1 (en) * 1976-06-24 1978-01-20 Rolls Royce FUEL CIRCUIT CONTROL SYSTEM FOR AIRPLANE TURBOREACTOR

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