GB1416464A - Jet propulsion engines - Google Patents

Jet propulsion engines

Info

Publication number
GB1416464A
GB1416464A GB1000273A GB1000273A GB1416464A GB 1416464 A GB1416464 A GB 1416464A GB 1000273 A GB1000273 A GB 1000273A GB 1000273 A GB1000273 A GB 1000273A GB 1416464 A GB1416464 A GB 1416464A
Authority
GB
United Kingdom
Prior art keywords
thrust
thrust reversal
zones
slots
reversal
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
GB1000273A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1416464A publication Critical patent/GB1416464A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B64C25/423—Braking devices acting by reaction of gaseous medium
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1416464 Propulsion jet thrust reversal SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 1 March 1973 [6 March 1972] 10002/73 Heading B7G [Also in Division F2] A jet propulsion engine, which in the forward thrust position discharges a gas flow to the rear, is located within a nacelle 8 with an after-body 9 having lateral openings 10 through which at least a major portion of the gas flow may be diverted with a forward component of velocity for thrust reversal, and those zones 11 of the after-body which are circumferentially between the openings 10 are provided with means for causing the external air flow Fe to break away from the wall of the nacelle during thrust reversal. It is stated that in the forward thrust position, because of the taper of the after-body, the external air flow is recompressed, giving a thrust (negative drag), and that this also occurs in the regions to the rear of the zones 11, reducing the braking effect, during thrust reversal. Therefore in the thrust reversal position air fi may be injected into the external air flow to cause it to break away, giving rise to lowpressure turbulence 21 and increasing drag. This air fi may be provided from circumferentially extending slots 15a-15d in the zones 11, of which the slots 15b, 15d are covered by the thrust-reversing obstacles 12 in the forward thrust position, Fig. 1 (not shown), and the slots 15a, 15c are closed by flaps 16 which are linked to toothed sectors 14 controlling the obstacles 12. Or, Fig. 2a (not shown), both the openings 10 and slots (115) may be uncovered in the thrust reversal position by an axially movable fairing (109). In both these embodiments the injected air is tapped from the main flow through the engine; alternatively, Fig. 3 (not shown), air bled from compressor (3) may be supplied to slots (215) in the zones 11 during thrust reversal. Alternatively the external air flow may be disturbed by flaps (315), Figs. 4, 5 (not shown), which are caused to protrude from the external wall of the after-body in the zones 11 during thrust reversal.
GB1000273A 1972-03-06 1973-03-01 Jet propulsion engines Expired GB1416464A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7207726A FR2174672B1 (en) 1972-03-06 1972-03-06

Publications (1)

Publication Number Publication Date
GB1416464A true GB1416464A (en) 1975-12-03

Family

ID=9094694

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1000273A Expired GB1416464A (en) 1972-03-06 1973-03-01 Jet propulsion engines

Country Status (3)

Country Link
DE (1) DE2310921C3 (en)
FR (1) FR2174672B1 (en)
GB (1) GB1416464A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117720A (en) * 1981-02-28 1983-10-19 Rolls Royce Gas turbine engine having a thrust spoiler
GB2295994A (en) * 1994-12-14 1996-06-19 Short Brothers Plc Drag device for engine nacelle

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1506588A (en) * 1975-10-11 1978-04-05 Rolls Royce Gas turbine engine power plants for aircraft
FR2661714B1 (en) * 1990-05-03 1994-06-17 Snecma DEVICE FOR SUPPLYING FUEL TO A GAS TURBINE.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117720A (en) * 1981-02-28 1983-10-19 Rolls Royce Gas turbine engine having a thrust spoiler
GB2295994A (en) * 1994-12-14 1996-06-19 Short Brothers Plc Drag device for engine nacelle
US5730393A (en) * 1994-12-14 1998-03-24 Short Brothers Plc Aircraft propulsive power unit
GB2295994B (en) * 1994-12-14 1998-10-14 Short Brothers Plc Aircraft propulsive power unit

Also Published As

Publication number Publication date
FR2174672A1 (en) 1973-10-19
FR2174672B1 (en) 1975-06-13
DE2310921A1 (en) 1973-09-20
DE2310921B2 (en) 1978-11-23
DE2310921C3 (en) 1979-07-19

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee