DE452147C - Compression regulator for aircraft engines - Google Patents
Compression regulator for aircraft enginesInfo
- Publication number
- DE452147C DE452147C DEL66094D DEL0066094D DE452147C DE 452147 C DE452147 C DE 452147C DE L66094 D DEL66094 D DE L66094D DE L0066094 D DEL0066094 D DE L0066094D DE 452147 C DE452147 C DE 452147C
- Authority
- DE
- Germany
- Prior art keywords
- pressure
- compression
- aircraft engines
- working
- control
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D15/00—Varying compression ratio
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D2700/00—Mechanical control of speed or power of a single cylinder piston engine
- F02D2700/03—Controlling by changing the compression ratio
- F02D2700/035—Controlling by changing the compression ratio without modifying the volume of the compression space, e.g. by changing the valve timing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Fluid Pressure (AREA)
Description
DEUTSCHES REICHGERMAN EMPIRE
AUSGEGEBEN AM 7. NOVEMBER 1927ISSUED NOVEMBER 7, 1927
REICHSPATENTAMTREICH PATENT OFFICE
PATENTSCHRIFTPATENT LETTERING
KLASSE 46 b2 GRUPPE 18CLASS 46 b 2 GROUP 18
L 66094 1146b2 Tag der Bekanntmachung fiber die Erteilung des Patents: 20. Oktober ig2j.L 66094 1146b 2 Date of the announcement about the grant of the patent: October 20th ig2j.
. Prosper L'Orange in Mannheim. Kompressionsregler für Flugmotoren. Patentiert im Deutschen Reiche vom 13. Juni 1926 ab. . Prosper L'Orange in Mannheim. Compression regulators for aircraft engines. Patented in the German Empire on June 13, 1926.
Es ist bekannt, den Kompressionsdruck von Flugmotoren für große Höhen dadurch zu regulieren, daß der Druckunterschied zwischen dem konstanten Druck in einer Membrandose und dem sich ändernden Außenluftdruck zur Betätigung einer Drosselklappe oder zur Verstellung der Öffnungszeit der Ventile verwendet wird.It is known to reduce the compression pressure of aircraft engines for high altitudes to regulate that the pressure difference between the constant pressure in a diaphragm box and the changing outside air pressure to operate a throttle valve or to adjust the opening time of the Valves is used.
Wenn nun einmal eine solche Dose undicht wird oder sonstwie die Drucke sich ausgleichen, versagt diese Art Vorrichtungen.If one of these cans leaks or the pressures balance out in some other way, these types of devices fail.
Gegenstand der vorliegenden Erfindung istThe subject of the present invention is
eine Vorrichtung, die diesen Nachteil vermeidet, indem sie die Regulierung des Motors mit Hilfe des immer vorhandenen Drucks im Motor selber, der ja auch gerade das zu Regulierende ist, betätigt.a device that avoids this disadvantage by regulating the motor with the help of the pressure that is always present in the engine itself, which is also responsible for that Regulating is actuated.
Zu diesem Zweck wird an einer bestimmten Stelle des Diagramms (Abb. i) der Druck abgenommen. Dieses kann der Maximaldruck sein (bei d). Dann hat man den Vorteil, daß man keine gesteuerte Öffnung braucht, aber den Nachteil, daß das Rückschlagventil unter der Wirkung der Explosionsstichflamme steht, wodurch erfahrungsgemäß leicht ein Verbrennen bzw. eine Ungänglichkeit des Ventils eintritt.For this purpose, the pressure is removed at a certain point on the diagram (Fig. I). This can be the maximum pressure (at d). Then you have the advantage that you do not need a controlled opening, but the disadvantage that the check valve is under the action of the explosive flame, which experience has shown that burning or inoperability of the valve easily occurs.
Dieses würde man vermeiden, wenn man den Druck an einer Stelle der Kompressionslinie b-c abnimmt. Dabei müßte aber das Ventil gesteuert sein, und es kämen explosible Gasgemische in den Druckraum. Man kann jedoch auch den Arbeitsdruck nach vollendeter Verbrennung an einer Stelle, wo das Ventil nicht mehr der Explosionsstichflamme ausgesetzt ist, also auf der Expansionslinie des Diagramms (bei Z) abnehmen, wobei die Steuerung des Ventils sich vereinfacht und auch keine explosiblen Gase in den Druckraum kommen.This would be avoided by reducing the pressure at one point on the compression line bc . In this case, however, the valve would have to be controlled and explosive gas mixtures would enter the pressure chamber. However, you can also take the working pressure after complete combustion at a point where the valve is no longer exposed to the explosion flame, i.e. on the expansion line of the diagram (at Z), whereby the control of the valve is simplified and there are no explosive gases in the pressure chamber come.
Das Diagramm a-b-c-d-e-b-a zeigt ein normales Viertaktexplosionsdiagramm für den Luftdruck in größeren Höhen, z. B. bei o,2 Atm. Luftdruck. Wählt man nun einen Punkt der Expansionslinie nach der zuletzt angegebenen Möglichkeit, der von der eigentliehen Verbrennungszeit nicht mehr getroffen wird und andererseits so hohen Druck als möglich besitzt, z. B. um den Weg .r vom Hubende entfernt, so kann dieser Druck durch eine öffnung im Zylindermantel, die vom Kolben an dem betreffenden Punkte freigegeben wird, ein der jeweiligen Höhe des Expansionsdruckes entsprechender Druck, abgezapft werden.The diagram abcdeba shows a normal four-stroke explosion diagram for the air pressure at higher altitudes, e.g. B. at 0.2 atm. Air pressure. If you now choose a point on the expansion line according to the last option indicated, which is no longer affected by the actual combustion time and which, on the other hand, has as high a pressure as possible, e.g. B. by the distance .r from the end of the stroke, this pressure can be drawn off through an opening in the cylinder jacket that is released by the piston at the relevant point, a pressure corresponding to the respective level of the expansion pressure.
Steigt beim Sinken des Flugzeuges in tieferen Luftschichten der Luftdruck um χ Atm., z. B. 0,8 Atm., so würde der Druck im Diagramm um ein Vielfaches von x, bei obigemBeispiel um etwa das 2ofache, steigen.When the aircraft descends, the air pressure changes in deeper layers of the air χ Atm., e.g. B. 0.8 atm., The pressure in the diagram would be a multiple of x, at above example by about 2 times.
Sobald er jedoch um mehr als x' gestiegen ist, beginnt die Regulierung zu wirken, die in Abb. 2 abgebildet ist, bis bei höchstem Luftdruck das gestrichelte Diagramm a'-f- b'-f'-c'-d'-e'-b'-f'-a' entsteht.However, as soon as it has risen by more than x ', the regulation begins to act, which is shown in Fig. 2, until at the highest air pressure the dashed diagram a'-f- b'-f'-c'-d'-e '-b'-f'-a' is created.
Die Regulierung besteht darin, daß der hei Z durch die Öffnung im Zylindermantel 0 abgezapfte Gasdruck durch ein RückschlagThe regulation consists in that the gas pressure drawn off through the opening in the cylinder jacket 0 is caused by a kickback
ventil U, welches vermittels einer Feder geschlossen wird, in den Regulierzylinder B gelangt und auf den Kolben L wirkt. Dieser wird in dem Maß, wie der Druck in E steigt, 5o gegen eine Feder F abwärts bewegt und stellt durch Stange P, Winkelhebel H und Muffe Q die Steuerwelle W so ein, daß der Schluß des Einlaßventils, welches vom schrägen Nocken N und der Rolle R betätigt wird, 65 früher erfolgt und damit die Kompression kleiner wird. Der maximale Druckzuwachs kann dann bei Z nicht mehr als x' Atm. betragen, bei welchen die Nockenwelle auf frühesten Schluß eingestellt wird, und es ist 7° leicht, ihn in erträglichen Grenzen, etwa 2 Atm., zu halten. Durch das kleine Ventil Y wird eine dauernde kleine Undichtheit des Zylinders E bewirkt, durch welche der Gasdruck in E bald wieder sinkt, wenn er 75 nicht gespeist wird, also beim Steigen des Flugzeuges.valve U, which is closed by means of a spring, enters the regulating cylinder B and acts on the piston L. As the pressure in E rises, this is moved 5o downwards against a spring F and, by means of rod P, angle lever H and sleeve Q, sets the control shaft W so that the inlet valve closes, which is controlled by the inclined cam N and the Roller R is actuated, 65 takes place earlier and thus the compression is smaller. The maximum pressure increase at Z can then not exceed x 'Atm. in which the camshaft is set to the earliest end, and it is 7 ° easy to keep it within tolerable limits, about 2 atm. The small valve Y causes a permanent small leak in the cylinder E , through which the gas pressure in E soon drops again if it is not fed, i.e. when the aircraft is climbing.
Claims (2)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEL66094D DE452147C (en) | 1926-06-13 | 1926-06-13 | Compression regulator for aircraft engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEL66094D DE452147C (en) | 1926-06-13 | 1926-06-13 | Compression regulator for aircraft engines |
Publications (1)
Publication Number | Publication Date |
---|---|
DE452147C true DE452147C (en) | 1927-11-07 |
Family
ID=7281505
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DEL66094D Expired DE452147C (en) | 1926-06-13 | 1926-06-13 | Compression regulator for aircraft engines |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE452147C (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1001049B (en) * | 1951-06-16 | 1957-01-17 | Ralph Miller | Internal combustion engine |
DE1035401B (en) * | 1953-06-17 | 1958-07-31 | Solex Sarl | Control device for two-stroke internal combustion engines with precompression in the crankcase |
DE1054780B (en) * | 1953-12-29 | 1959-04-09 | Nsu Werke Ag | Four-stroke internal combustion engine with regulation of the compression chamber size |
DE1129764B (en) * | 1955-03-30 | 1962-05-17 | Adalbert Steusloff | Method and device for charging internal combustion engines, in particular for motor vehicles |
-
1926
- 1926-06-13 DE DEL66094D patent/DE452147C/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1001049B (en) * | 1951-06-16 | 1957-01-17 | Ralph Miller | Internal combustion engine |
DE1035401B (en) * | 1953-06-17 | 1958-07-31 | Solex Sarl | Control device for two-stroke internal combustion engines with precompression in the crankcase |
DE1054780B (en) * | 1953-12-29 | 1959-04-09 | Nsu Werke Ag | Four-stroke internal combustion engine with regulation of the compression chamber size |
DE1129764B (en) * | 1955-03-30 | 1962-05-17 | Adalbert Steusloff | Method and device for charging internal combustion engines, in particular for motor vehicles |
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