DE589658C - Cooling device for internal combustion engines in vehicles and aircraft - Google Patents
Cooling device for internal combustion engines in vehicles and aircraftInfo
- Publication number
- DE589658C DE589658C DES106369D DES0106369D DE589658C DE 589658 C DE589658 C DE 589658C DE S106369 D DES106369 D DE S106369D DE S0106369 D DES0106369 D DE S0106369D DE 589658 C DE589658 C DE 589658C
- Authority
- DE
- Germany
- Prior art keywords
- aircraft
- cooling device
- internal combustion
- suction channel
- combustion engines
- 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
Links
- 238000001816 cooling Methods 0.000 title claims description 10
- 238000002485 combustion reaction Methods 0.000 title claims description 6
- 230000033001 locomotion Effects 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000012528 membrane Substances 0.000 claims 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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
- F01P7/00—Controlling of coolant flow
- F01P7/02—Controlling of coolant flow the coolant being cooling-air
- F01P7/10—Controlling of coolant flow the coolant being cooling-air by throttling amount of air flowing through liquid-to-air heat exchangers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Kühleinrichtung für Brennkraftmaschinen in Fahr- und Flugzeugen Bei Brennkraftmaschinen in Fahr- und Flugzeugen mit Gebläsekühlung muß der Aufwand für die Kühlung möglichst gering sein, damit nicht ein zu großer Teil der Motorleistung dafür verbraucht wird.Cooling device for internal combustion engines in vehicles and aircraft Internal combustion engines in vehicles and aircraft with fan cooling must be the expense for the cooling should be as low as possible, so that not too much of the engine output is consumed for this.
Wenn man die Öffnung des Saugkanals für das Gebläse in die Fahrtrichtung legt, um die Fahrtgeschwindigkeit auszunutzen, so strömt die Luft nur dann wiederstandslos dem Gebläse zu, wenn das Gebläse die zugeführte Luftmenge vollständig bewältigen kann. Ist im Saugkanal Überdruck vorhanden, so wirkt er hemmend auf die Fortbewegung des Fahrzeuges oder Flugzeuges. Der Leistungsaufwand für die Fortbewegung wird dagegen kleiner, wenn kein Überdruck vorhanden ist. -- Andererseits muß beim Betrieb einer Brennkraftmaschine mit Gebläsekühlung die zugeführte Kühlluftmenge der Erwärmung angepaßt sein.If you look at the opening of the suction channel for the fan in the direction of travel sets in order to take advantage of the driving speed, only then does the air flow without resistance to the fan when the fan fully cope with the amount of air supplied can. If there is overpressure in the suction channel, it has an inhibiting effect on locomotion of the vehicle or aircraft. The effort required for locomotion is on the other hand smaller if there is no overpressure. - On the other hand, when operating a Internal combustion engine with fan cooling the amount of cooling air supplied for heating be adjusted.
Erfindungsgemäß verhindert man die Entstehung von Staudruck in der Saugöffnung dadurch, daß ein Teil der Rumpfhaut des Fahr- oder Flugzeugs als Saugkanal ausgebildet und um eine Drehachse schwenkbar gemacht wird, wodurch sein Querschnitt geregelt werden kann.According to the invention prevents the formation of back pressure in the Suction opening in that part of the fuselage skin of the vehicle or aircraft acts as a suction channel is formed and made pivotable about an axis of rotation, whereby its cross section can be regulated.
Auf der Zeichnung ist eine Ausführungsform der Erfindung an einem Flugzeug schematisch dargestellt.In the drawing, an embodiment of the invention is on one Airplane shown schematically.
i ist das Kurbelgehäuse einer Brennkraftmaschine mit einer Anzahl nach unten liegender Zylinder j, die durch ein Gebläse 3 gekühlt werden. Dieses Gebläse wird durch ein Übersetzungsgetriebe von der Kurbelwelle angetrieben. Die Luft wird dem Gebläse durch den Saugkanal 4 zugeführt. In dem Kanal ist ein Staurohr 5 angebracht, von dem aus eine Leitung 6 zu einem Zylinder 7 führt. In diesem Zylinder- liegt ein Kolben 8, den eine Feder g nach links zu verschieben sucht. Der Kolben ist unter Vermittlung eines Gestänges io, io' mit dem um eine Drehachse ii schwenkbaren Saugkana14 verbunden.'er Saugkanal a kann um diese Drehachse mehr öder weniger_aus der Umrißfläche des Flug- zeugrumpfes i2 herausgeschwenkt oder herangezogen werden: Ist der Staudruck im Innern des Luftführungsrohres 4 zu groß, so wird er über das Staurohr 5 und die Leitung 6 in den Zylinder 7 übertragen. Er verschiebt dadurch den Kolben 8 entgegen der Feder g nach rechts. Infolgedessen wird der Luftzuführungskanal4 mit Hilfe der Gestänge io und io' weiter an die Umrißfläche des Flugzeugrumpfes 12 herangezogen. Dadurch verkleinert sich die Eintrittsöffnung des Saugkanals, und der Staudruck nimmt ab.i is the crankcase of an internal combustion engine with a number of cylinders j lying down, which are cooled by a fan 3. This fan is driven by the crankshaft through a transmission gear. The air is supplied to the fan through the suction channel 4. A pitot tube 5 is attached in the channel, from which a line 6 leads to a cylinder 7. In this cylinder there is a piston 8 which a spring g seeks to move to the left. The piston is io through the intermediary of a linkage, io 'with about a rotational axis ii pivotable Saugkana14 verbunden.'er suction channel a k ann to this axis of rotation more barren weniger_aus the Umrißfläche of the aircraft fuselage to be swung out or used i2: Is the dynamic pressure in the interior of the air duct 4 is too large, it is transmitted into the cylinder 7 via the pitot tube 5 and the line 6. He thereby moves the piston 8 against the spring g to the right. As a result, the air supply duct 4 is drawn further to the contour surface of the aircraft fuselage 12 with the aid of the linkages io and io '. This reduces the size of the inlet opening of the suction channel and the back pressure decreases.
Um eine willkürliche Regelung von Hand zu ermöglichen, ist ein an der Stange io angreifender Handhebel 15 angebracht.To enable arbitrary manual control, an is on the rod io attacking hand lever 15 attached.
Die Regelung der Saugkanalöffnung in Abhängigkeit von der Erwärmung der Zylinder erfolgt mit Hilfe eines punktiert angedeuteten Ausdehnungsstabes 13, an dessen Stelle auch eine Bimetallfeder verwendet werden kann und der je nach seiner Länge über einen Hebel 14 den Saugkanal weiter aus dem Flugzeugrumpf herausschwenkt oder ihn heranzieht.The regulation of the suction channel opening depending on the heating the cylinder takes place with the help of an expansion rod 13 indicated by dotted lines, a bimetal spring can be used in its place and depending on its Length over a lever 14 pivots the suction channel further out of the aircraft fuselage or pull him up.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DES106369D DE589658C (en) | Cooling device for internal combustion engines in vehicles and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DES106369D DE589658C (en) | Cooling device for internal combustion engines in vehicles and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE589658C true DE589658C (en) | 1933-12-12 |
Family
ID=7527381
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DES106369D Expired DE589658C (en) | Cooling device for internal combustion engines in vehicles and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE589658C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE901135C (en) * | 1940-09-08 | 1954-01-07 | Daimler Benz Ag | Air ducting on aircraft engines with a fairing surrounding the engine cooler or the engine |
-
0
- DE DES106369D patent/DE589658C/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE901135C (en) * | 1940-09-08 | 1954-01-07 | Daimler Benz Ag | Air ducting on aircraft engines with a fairing surrounding the engine cooler or the engine |
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