DE744788C - Cooling system for aircraft internal combustion engines - Google Patents

Cooling system for aircraft internal combustion engines

Info

Publication number
DE744788C
DE744788C DEM150111D DEM0150111D DE744788C DE 744788 C DE744788 C DE 744788C DE M150111 D DEM150111 D DE M150111D DE M0150111 D DEM0150111 D DE M0150111D DE 744788 C DE744788 C DE 744788C
Authority
DE
Germany
Prior art keywords
internal combustion
combustion engines
cooler
cooling system
aircraft internal
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
DEM150111D
Other languages
German (de)
Inventor
Dipl-Ing Gerhard Caroli
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.)
Messerschmitt AG
Original Assignee
Messerschmitt AG
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 Messerschmitt AG filed Critical Messerschmitt AG
Priority to DEM150111D priority Critical patent/DE744788C/en
Application granted granted Critical
Publication of DE744788C publication Critical patent/DE744788C/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
    • F01P11/14—Indicating devices; Other safety devices

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid-Pressure Circuits (AREA)

Description

Kühlanlage für Flugzeugbrennkraftmaschinen Bei KriegsfluZzeugen ist ein großer Teil von Notlandungen darauf zurückzuführen, daß der Kühler durch einen Schuß verletzt wird und die Maschine dadurch ausfällt. Um diese Gefahr einzuschränken, ist schon vorgeschlagen worden, den Kühler in mehrere parallele Zweige zu unterteilen und durch handbezvegte Ventile jeden dieser Zweige abschaltbar zu machen; in der Rückleitung sind auch an Stelle handbewegter Ventile selbsttätige Rückschlagklappen angeordnet. Die in der Zuleitung stets beibehaltene Handbewegung isc aber vollkommen unzureichend, da der Flugzeugführer gerade in solchen kritischen Augenblicken keine Zeit hat, sich um die Kühlanlage zu kümmern, eine Beschädigung sofort zu bemerken, festzustellen, welcher Kühlerteil beschädigt ist und diesen dann abzuschalten. Bei größeren Verletzungen kann aber schon. im Bruchteil einer Minute ehre erliebliche Menge von Kühlflüssigkeit verlorengegangen sein, so daß ein Ausfall der Maschine doch unvermeidlich ist.Cooling system for aircraft internal combustion engines a large part of emergency landings is due to the cooler being replaced by a Shot is injured and the machine fails. To limit this danger it has already been proposed to divide the cooler into several parallel branches and to make each of these branches switchable by hand-operated valves; in the Return lines are also automatic non-return valves instead of manually operated valves arranged. The hand movement, which is always maintained in the supply line, is, however, perfect inadequate, since the pilot does not have any at such critical moments Has time to take care of the cooling system, to notice any damage immediately, determine which part of the cooler is damaged and then switch it off. at larger injuries can be. honorable in a fraction of a minute Amount of coolant has been lost, causing machine failure but is inevitable.

Gemäß der Erfindung wird nun bei einem in mehrere parallele Zweige unterteilten Kühler mit je einem Rückschlagventil an der Austrittsseite jedes Kühlers zusätzlich an jeder Kühlerzuleitung noch ein selbsttätiges Roltrbruchventil angebracht. Tritt nun eine Verletzung ein, so schließt das Rohrbruchventil, das im übrigen in an sich bekannter Art gebaut sein kann, durch die erhöhte Strömungsgeschwindigkeit in der Zuleitung und das Rücksrhlagventil durch die rückströmende Kühlflüssigkeit in der Ableitung, so daß die verletzte Stelle sofort beiderseits vom Kühlkreislauf abgeschaltet und ein weiterer Flüssigkeitsverlust verhindert ist.According to the invention, there is now one in several parallel branches subdivided cooler with a check valve on the outlet side of each cooler In addition, an automatic roll break valve is attached to each cooler supply line. If an injury occurs, the pipe rupture valve closes, which is also in can be built of a known type, due to the increased flow velocity in the supply line and the return valve through the returning cooling liquid in the discharge, so that the injured point immediately on both sides of the cooling circuit switched off and a further loss of fluid is prevented.

Die. Abbildung zeigt planmäßig ein Ausführungsbeispiel der Erfindung. i ist die Maschine mit der Kühlwasserpumpe, 2 und 3 sind die beiden Kühler, deren Anzahl jedoch beliebig sein kann. In der Zuleitung von der Maschine i zu jedem der Kühler 3 ist ein Rohrbruchventil4 eingeschaltet, das bei gewöhnlicher Strömungsgeschwindigkeit offen bleibt, sich aber bei erhöhter Strömungsgeschwindigkeit schließt. Ebenso enthält jede der Leitungen von den Kühlerteilen .3 zur Kühlflüssigkeitspumpe 2 in für sich allein bekannter Weise ein Rückschlagventil 5.The. The figure shows a planned embodiment of the invention. i is the machine with the cooling water pump, 2 and 3 are the two coolers whose However, the number can be arbitrary. In the supply line from the machine i to each of the Cooler 3 is switched on a pipe rupture valve 4, which at normal flow rate remains open, but closes when the flow velocity increases. Also contains each of the lines from the cooler parts .3 to the coolant pump 2 in itself a check valve 5 in a known manner.

Claims (1)

PATENTANSPRUCH: Sicherheitsvorrichtung zum selbsttätgen Abschalten von Kühlern zur Verhütung von Wasserverlust bei Kühlerundichtigkeit in Kühlanlagen für Flugzeugbrennkraftmaschinen mit Flüssigkeits- oder Verdampfungskühlung mit mehreren parallel geschalteten Kühlern, dadurch gekennzeichnet, daß in jeder Kühleraustrittsleitung in -an sieh bekannter Weise ein Rückschlagventil (5j und in jeder Zuflußleitung in an sich bekannter Weise ein Rohrbrttchventil angeordnet ist. Zur Abgrenzung des Anmeldungsgegenstandes vom Stand der Technik sind im Erteilungsverfahren folgende Druckschriften in Betracht gezogen worden: französische Patentschriften Nr.5:z6.19o. 589 163. 729 523.PATENT CLAIM: Safety device for the automatic shutdown of coolers to prevent water loss in the event of cooler leaks in cooling systems for aircraft internal combustion engines with liquid or evaporative cooling with several coolers connected in parallel, characterized in that in each cooler outlet line a check valve (5j and in each inflow line in a manner known per se) In order to distinguish the subject of the application from the state of the art, the following publications have been considered in the granting procedure: French patent specifications No. 5: December 6, 1990, 589 163, 729 523.
DEM150111D 1940-06-27 1940-06-27 Cooling system for aircraft internal combustion engines Expired DE744788C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEM150111D DE744788C (en) 1940-06-27 1940-06-27 Cooling system for aircraft internal combustion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEM150111D DE744788C (en) 1940-06-27 1940-06-27 Cooling system for aircraft internal combustion engines

Publications (1)

Publication Number Publication Date
DE744788C true DE744788C (en) 1944-01-25

Family

ID=7336809

Family Applications (1)

Application Number Title Priority Date Filing Date
DEM150111D Expired DE744788C (en) 1940-06-27 1940-06-27 Cooling system for aircraft internal combustion engines

Country Status (1)

Country Link
DE (1) DE744788C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6870107B2 (en) * 2001-01-19 2005-03-22 Daume Patentbesitzgesellschaft Mbh & Co. Kg Device for electrically contacting a sectionally insulated external conductor of a coaxial cable

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR526490A (en) * 1916-11-06 1921-10-08 Jean Marie Frugere Radiator with variable cooling power and constant flow
FR589163A (en) * 1924-11-19 1925-05-25 Liore & Olivier Ets Radiator for airplanes and other vehicles
FR729523A (en) * 1931-03-20 1932-07-26 Cooling process for thermal engines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR526490A (en) * 1916-11-06 1921-10-08 Jean Marie Frugere Radiator with variable cooling power and constant flow
FR589163A (en) * 1924-11-19 1925-05-25 Liore & Olivier Ets Radiator for airplanes and other vehicles
FR729523A (en) * 1931-03-20 1932-07-26 Cooling process for thermal engines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6870107B2 (en) * 2001-01-19 2005-03-22 Daume Patentbesitzgesellschaft Mbh & Co. Kg Device for electrically contacting a sectionally insulated external conductor of a coaxial cable

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