GB822472A - Improvements in or relating to jet propulsion nozzles - Google Patents

Improvements in or relating to jet propulsion nozzles

Info

Publication number
GB822472A
GB822472A GB19181/56A GB1918156A GB822472A GB 822472 A GB822472 A GB 822472A GB 19181/56 A GB19181/56 A GB 19181/56A GB 1918156 A GB1918156 A GB 1918156A GB 822472 A GB822472 A GB 822472A
Authority
GB
United Kingdom
Prior art keywords
jet pipe
members
jet
pivoted
axis
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
GB19181/56A
Inventor
David Morris Brown
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
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB19181/56A priority Critical patent/GB822472A/en
Publication of GB822472A publication Critical patent/GB822472A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Advancing Webs (AREA)

Abstract

822,472. Jet propulsion nozzles. ROLLSROYCE Ltd. June 20, 1957 [June 20, 1956], No. 19181/56. Class 110 (3). [Also in Group XXXIII] A jet propulsion nozzle comprises a pair of members having a cross-section similar to that of part of the downstream end of the jet pipe and each of which is pivoted about an axis transverse to the jet pipe so that it is capable of being set in a first position on which it forms a smooth downstream in continuation of the jet pipe without reducing the cross-sectional area of flow, and in a second position in which its upstream edge lies inwardly of the wall of the jet pipe in which it divides the jet into separate streams. A cylindrical jet pipe 50 has a pair of part cylindrical members 51 mounted to pivot about an axis 52 from a first position, in which the members 51 form a smooth continuation of the jet pipe 50 to a second position, Fig. 2, in which the leading edge of each of the members is swung inwards until it lies between the jet pipe axis 53 and the periphery of the jet pipe. In the second position the members 51 divide the jet stream into three separate streams to produce a silencing effect. Preferably the outer streams diverge from the axial direction at an angle of 20 to 25 degrees. The members 51 may also be pivoted into a third position in which the trailing edges are in abutment. In this position the gas flowing through the jet pipe is deflected to flow in a reverse direction. In a modification, Fig. 4 (not shown) the leading edges of the pivoted members 51 and the trailing edge of the jet pipe are increased in thickness so that a convergent-divergent nozzle is formed.
GB19181/56A 1956-06-20 1956-06-20 Improvements in or relating to jet propulsion nozzles Expired GB822472A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB19181/56A GB822472A (en) 1956-06-20 1956-06-20 Improvements in or relating to jet propulsion nozzles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB19181/56A GB822472A (en) 1956-06-20 1956-06-20 Improvements in or relating to jet propulsion nozzles

Publications (1)

Publication Number Publication Date
GB822472A true GB822472A (en) 1959-10-28

Family

ID=10125094

Family Applications (1)

Application Number Title Priority Date Filing Date
GB19181/56A Expired GB822472A (en) 1956-06-20 1956-06-20 Improvements in or relating to jet propulsion nozzles

Country Status (1)

Country Link
GB (1) GB822472A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2526872A1 (en) * 1982-05-17 1983-11-18 Hurel Dubois Avions Const THRUST INVERTER WITH DOOR IN PARTICULAR FOR A REACTION AIRCRAFT ENGINE

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2526872A1 (en) * 1982-05-17 1983-11-18 Hurel Dubois Avions Const THRUST INVERTER WITH DOOR IN PARTICULAR FOR A REACTION AIRCRAFT ENGINE

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