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Publication numberUS2330622 A
Publication typeGrant
Publication dateSep 28, 1943
Filing dateMar 27, 1940
Priority dateApr 1, 1939
Publication numberUS 2330622 A, US 2330622A, US-A-2330622, US2330622 A, US2330622A
InventorsReinhard Ramshorn
Original AssigneeReinhard Ramshorn
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Guiding and controlling device for cowlings
US 2330622 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

Sept. 28, 1943. R. RAMSIHORNQ GUIDING AND CONTROLLING DEVICE FOR COWLINGS Filed March 27, 1940 UNITED STATES PATENT OFFICE GUIDING AND CONTROLLING DEVICE FOR COWLINGS Reinhard Ramshorn, Munich, Grafelfing, Germany; vested in the Alien Property Custodian Application March 27, 1940, Serial No. 326,140 In Germany April 1, 1939 5 Claims.

The invention relates to means for guiding and controlling the air entering the fairing or engine cowling of air-cooled internal combustion engines, particularly for aircraft, preferably radial engines.

An object of this invention is to provide an improved cowling which not only has a favorable external aerodynamic shape, but also improves the guiding of cooling air within the cowling.

Another object of this invention is to provide an improved cowling having reduced air resistance and which, at the same time, carries cooling air back to the engine without production of unfavorable and disturbing eddies and vortices.

A further object of this invention is the provision of an engine cowling having a section rotating with the propeller blades and constructed with an improved, adjustable cooling air inlet opening.

A more specific object of this invention is the provision of an engine cowling for aeroplanes, having a section rotatable with the propeller, and constructed with internal air-accelerating baffles for supplying cooling air to the engine.

These and other features of the invention will be best understood and appreciated from the following description of a preferred embodiment thereof described for purposes of illustration and shown in the accompanying drawing, in which:

The single figure is a longitudinal view, partially in cross-section, of the forward part of an engine cowling in accordance with the present invention.

The engine cowling arranged symmetrically with respect to the longitudinal axis I of the engine (not shown), includes a stationary cowling part 2 surrounding the cylinders and the part 4 rotating with the propeller blades 3. A cylindrical wall 5 is mounted co-axially within the part 4. A cap 6, capable of being displaced in the direction of axis I for controlling the inlet cross-sectional area of the annular conduit I defined by the cowling part 4 and the wall 5, is slidably mounted on the said wall 5. The baflles B and the supporting blades I surrounding the blade butt ends 9 serve at the same time to interconnect and mutually support the walls 4 and of the annular conduit I. The bafiles 8 and the blades ID are preferably arranged obliquely to the longitudinal axis I in such a manner that they also serve as blowers, thus effecting an acceleration of the air entering the cowling 4 and permitting a reduction of the power to be delivered to the fan II. The fan II, of course, can also be omitted.

In this manner, according to the invention all parts are of low air resistance and of suitable construction, and the blade butt ends 9, wellfaired, revolve in a directed air current, so that a far-reaching reduction of the profile drag and thus a remarkable increase in efficiency is obtained, which results in an increase of speed of the vehicle in question. In this respect, further, it has proved advantageous if the stationary part 2 of the cowling somewhat overlaps the part 4 in order that the pressure still existing in the boundary layer as far as possible compensate the interior pressure, and no formation of vortices or thickening of the boundary layer by the escaping air occurs at the point I2.

Although no means have been illustrated effecting movement of the cap 6 for adjusting the cross-sectional area of the air inlet, it will be obvious to those skilled in this art that this adjustment may be effected manually by means of suitable linkages or the like, or, using well-known apparatus, automatically by a suitable regulator responsive to engine temperature or, if desired, in accordance with charging pressure. The particular means for bringing about adjustment of the cap 6 does not, however, form part of the present invention, and accordingly will not be described or illustrated in detail.

Having described an illustrative embodiment of the invention, it is pointed out that various changes and modifications therein may be made without departing from the invention, it being intended that the patent shall cover, by suitable expression in the appended claims, all features of patentable novelty existing in the invention disclosed, as illustrated by the embodiment described.


1. In a cowling for engine-driven aircraft, the combination of a first stationary cowling section adapted to surround the engine proper, a propeller adapted to be driven by the engine, and a second cowling section rotatable with said propeller and positioned forwardly of said first cowling section, said second cowling section including a stream-lined outer wall open at both ends, surrounding and extending forwardly of the propeller butt ends, an inner cylindrical wall coaxial with and spaced from said outer wall to form an annular air-guiding space between the two walls, and baffles in said annular space interconnecting the two walls, said baiiles being so shaped as to assist in directing the oncoming air rearwardly through said annular space to said engine.

2. The combination according to claim 1, in

- which said baffles comprise suitably shaped plates covering that portion of the propeller butt ends in the annular space between said walls.

3. The combination according to claim 1, in which said baifies are shaped as air-accelerating blades.

4. The combination according to claim 1, in combination with baffling air-guiding blades surrounding that portion of the propeller butt ends 10 in the annular space between said walls, said baflles and said air-guiding blades being shaped as air-accelerating blades.

5. The combination according to claim 1, in combination with a stream-lined cap slidably adjustable upon and closing the forward end of said inner cylindrical wall for varying the cross-sectional area of the air inlet opening formed at the forward end of the two walls.


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2424839 *Sep 21, 1943Jul 29, 1947B F Sturtevant CoSpin vanes control device for cooling fans in aircraft engines
US2425088 *Sep 13, 1943Aug 5, 1947Curtiss Wright CorpFan blade and mounting means therefor
US2427166 *Jan 22, 1945Sep 9, 1947Gen Motors CorpPropeller blade fairing
US2456151 *Mar 29, 1943Dec 14, 1948Curtiss Wright CorpAircraft engine cooling system
US2476643 *Jul 1, 1944Jul 19, 1949United Aircraft CorpBy-pass system for cooling fans
US2529103 *Feb 13, 1946Nov 7, 1950Curtiss Wright CorpSpinner deicing system
US2580789 *Nov 5, 1945Jan 1, 1952United Aircraft CorpAdjustable propeller cuff
US2605851 *Nov 30, 1946Aug 5, 1952Chrysler CorpAir intake for aircraft turbopropeller power plant
US2913055 *Sep 1, 1950Nov 17, 1959Thomas E QuickPropulsion device
US3279415 *Feb 25, 1965Oct 18, 1966Kiekhaefer CorpMarine propeller for discharging engine exhaust through the propeller hub
US7441724Sep 19, 2005Oct 28, 2008Aurora Flight Sciences CorporationSystem and method for controlling a roll rate of a torsionally-disconnected freewing aircraft
US7559191Sep 19, 2005Jul 14, 2009Aurora Flight Sciences CorporationDucted spinner for engine cooling
US8001764Sep 19, 2005Aug 23, 2011Aurora Flight Sciences CorporationVibration isolation engine mount system and method for ducted fans
US8667775 *Aug 5, 2009Mar 11, 2014The Boeing CompanyReverse flow engine core having a ducted fan with integrated secondary flow blades
US20040179941 *Feb 10, 2004Sep 16, 2004Dimitrie NegulescuTurboprop engine with co-rotating two-stage high-performance propeller
US20060065776 *Sep 19, 2005Mar 30, 2006Robert ParksSystem and method for controlling a roll rate of a torsionally-disconnected freewing aircraft
US20060102780 *Sep 19, 2005May 18, 2006Robert ParksDucted spinner for engine cooling
US20060248873 *Sep 19, 2005Nov 9, 2006Robert ParksVibration isolation engine mount system and method for ducted fans
US20070221783 *Sep 19, 2005Sep 27, 2007Robert ParksAdaptive landing gear
WO2007001372A2 *Sep 19, 2005Jan 4, 2007Aurora Flight SciencesDucted spinner for engine cooling
WO2007001372A3 *Sep 19, 2005Apr 23, 2009Aurora Flight SciencesDucted spinner for engine cooling
U.S. Classification416/94, 123/41.65, 415/72, 416/193.00R
International ClassificationF01P7/02, F01P7/00
Cooperative ClassificationF01P7/02
European ClassificationF01P7/02