GB743492A - Improvements in jet propulsion engines including a plurality of intermittently operating combustion chambers - Google Patents

Improvements in jet propulsion engines including a plurality of intermittently operating combustion chambers

Info

Publication number
GB743492A
GB743492A GB6639/53A GB663953A GB743492A GB 743492 A GB743492 A GB 743492A GB 6639/53 A GB6639/53 A GB 6639/53A GB 663953 A GB663953 A GB 663953A GB 743492 A GB743492 A GB 743492A
Authority
GB
United Kingdom
Prior art keywords
air
nozzle
chamber
combustion chambers
combustion
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
GB6639/53A
Inventor
Jean Henri Bertin
Louis Alexandre Jules Bauger
Francois Gilbert Paris
Alexandre Achille Mihail
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB743492A publication Critical patent/GB743492A/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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines

Abstract

743,492. Generating combustion products under pressure. SOC. NATIONALE D' ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. March 10, 1953 [March 11, 1952; March 13,1952], No. 6639/53. Class 51 (1). [Also in Group XXVI] An intermittently operating combustion chamber has on one side a valve or other non-return device and on the other side an ejection tube which is of insufficient length to provide self filling of the chamber, the filling of the chamber being effected by a scavenging device which maintains, during normal operation of the unit, a total air pressure at the entry of the chamber greater than the static pressure at the outlet of the ejection tube. The jet propulsion engine, Fig. 1, has a pulsatory combustion space 1 having an inlet 2 fitted with a non- return valve 2a, which may be of the aerodynamic type as described in Specification 660,144, [Group XXIX], and a convergent ejection nozzle 3. The length of the nozzle 3 is of the order of magnitude of the space 1 and should not exceed 1.0 to 1.5 times this length. Air is supplied to the space 1 by a blower 5 driven by an engine 7 which also drives through a variable speed device 7a a fuel injection pump 4a and an interrupter 8b for the sparking plug 8. The frequency of operation of the combustion chamber and thus the power output may be varied by adjustment of the device 7a. In a modification the blower 5 is dispensed with and the air is supplied to a number of combustion chambers through a diffuser when the chamber is mounted on a vehicle. The combustion chambers may be cooled by air passing through small holes in the end wall of the diffuser. The combustion chambers are enclosed in a fairing having a partition midway along its length in which the inlet valve or valves are mounted. The outlet area of the fairing is engaged so that the pressure drop between the two parts of the fairing is equal to the scavenging pressure required. To enable this arrangement to operate at various forward speeds the outlet of the fairing may be provided with a variable arc or'nozzle. In another modification, the scavenging air is supplied by a pulse jet unit acting in conjunction with a nozzle as an air compressor. When the combustion chambers are used as jet propulsion units the gases may be reheated before passing to the propulsion nozzle by a number of burners 60, Fig. 6, arranged in a circle in the propulsion nozzle 42, and disposed at the centre of conical diffusers 61 canaling the air. Specifications 653,629 and 711,281, [Group XXVI], are referred to.
GB6639/53A 1952-03-11 1953-03-10 Improvements in jet propulsion engines including a plurality of intermittently operating combustion chambers Expired GB743492A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR743492X 1952-03-11

Publications (1)

Publication Number Publication Date
GB743492A true GB743492A (en) 1956-01-18

Family

ID=9144207

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6639/53A Expired GB743492A (en) 1952-03-11 1953-03-10 Improvements in jet propulsion engines including a plurality of intermittently operating combustion chambers

Country Status (1)

Country Link
GB (1) GB743492A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3107486A (en) * 1959-11-16 1963-10-22 Hal R Linderfelt Hydrapulse motor
GB2416374A (en) * 2004-07-21 2006-01-25 Gen Electric Ducted gas turbine engine with pulse detonation tube(s)
WO2007025047A2 (en) * 2005-08-24 2007-03-01 University Of Cincinnati Performance improvements for pulse detonation engines using ejectors

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3107486A (en) * 1959-11-16 1963-10-22 Hal R Linderfelt Hydrapulse motor
GB2416374A (en) * 2004-07-21 2006-01-25 Gen Electric Ducted gas turbine engine with pulse detonation tube(s)
US7228683B2 (en) 2004-07-21 2007-06-12 General Electric Company Methods and apparatus for generating gas turbine engine thrust using a pulse detonator
GB2416374B (en) * 2004-07-21 2009-04-01 Gen Electric Methods and apparatus for generating gas turbine engine thrust
WO2007025047A2 (en) * 2005-08-24 2007-03-01 University Of Cincinnati Performance improvements for pulse detonation engines using ejectors
WO2007025047A3 (en) * 2005-08-24 2007-10-11 Univ Cincinnati Performance improvements for pulse detonation engines using ejectors

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