US2330622A - Guiding and controlling device for cowlings - Google Patents
Guiding and controlling device for cowlings Download PDFInfo
- Publication number
- US2330622A US2330622A US326140A US32614040A US2330622A US 2330622 A US2330622 A US 2330622A US 326140 A US326140 A US 326140A US 32614040 A US32614040 A US 32614040A US 2330622 A US2330622 A US 2330622A
- Authority
- US
- United States
- Prior art keywords
- cowling
- guiding
- air
- engine
- cowlings
- 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 - Lifetime
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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
Definitions
- 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.
- 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 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.
- 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 can also be omitted.
- 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 bariers being so shaped as to assist in directing the oncoming air rearwardly through said annular space to said engine.
- baffles comprise suitably shaped plates covering that portion of the propeller butt ends in the annular space between said walls.
Description
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.
Iclaim:
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.
REINHARD RAMSHORN.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2330622X | 1939-04-01 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2330622A true US2330622A (en) | 1943-09-28 |
Family
ID=7994860
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US326140A Expired - Lifetime US2330622A (en) | 1939-04-01 | 1940-03-27 | Guiding and controlling device for cowlings |
Country Status (1)
Country | Link |
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US (1) | US2330622A (en) |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2424839A (en) * | 1943-09-21 | 1947-07-29 | B F Sturtevant Co | Spin vanes control device for cooling fans in aircraft engines |
US2425088A (en) * | 1943-09-13 | 1947-08-05 | Curtiss Wright Corp | Fan blade and mounting means therefor |
US2427166A (en) * | 1945-01-22 | 1947-09-09 | Gen Motors Corp | Propeller blade fairing |
US2456151A (en) * | 1943-03-29 | 1948-12-14 | Curtiss Wright Corp | Aircraft engine cooling system |
US2476643A (en) * | 1944-07-01 | 1949-07-19 | United Aircraft Corp | By-pass system for cooling fans |
US2529103A (en) * | 1946-02-13 | 1950-11-07 | Curtiss Wright Corp | Spinner deicing system |
US2580789A (en) * | 1945-11-05 | 1952-01-01 | United Aircraft Corp | Adjustable propeller cuff |
US2605851A (en) * | 1946-11-30 | 1952-08-05 | Chrysler Corp | Air intake for aircraft turbopropeller power plant |
US2913055A (en) * | 1950-09-01 | 1959-11-17 | Thomas E Quick | Propulsion device |
US3279415A (en) * | 1965-02-25 | 1966-10-18 | Kiekhaefer Corp | Marine propeller for discharging engine exhaust through the propeller hub |
US20040179941A1 (en) * | 2003-02-10 | 2004-09-16 | Dimitrie Negulescu | Turboprop engine with co-rotating two-stage high-performance propeller |
US20060065776A1 (en) * | 2004-09-17 | 2006-03-30 | Robert Parks | System and method for controlling a roll rate of a torsionally-disconnected freewing aircraft |
US20060102780A1 (en) * | 2004-09-17 | 2006-05-18 | Robert Parks | Ducted spinner for engine cooling |
US20060248873A1 (en) * | 2004-09-17 | 2006-11-09 | Robert Parks | Vibration isolation engine mount system and method for ducted fans |
US20070221783A1 (en) * | 2004-09-17 | 2007-09-27 | Robert Parks | Adaptive landing gear |
US8667775B1 (en) * | 2009-08-05 | 2014-03-11 | The Boeing Company | Reverse flow engine core having a ducted fan with integrated secondary flow blades |
US20160298540A1 (en) * | 2015-04-13 | 2016-10-13 | United Technologies Corporation | Nose cone assembly and method of circulating air in a gas turbine engine |
US20170122207A1 (en) * | 2015-11-04 | 2017-05-04 | United Technologies Corporation | Engine with nose cone heat exchanger and radially outer discharge |
US20180045138A1 (en) * | 2015-02-09 | 2018-02-15 | United Technologies Corporation | Nose cone assembly and method of circulating air in a gas turbine engine |
US20180347463A1 (en) * | 2013-04-03 | 2018-12-06 | United Technologies Corporation | Gas turbine engine de-icing system |
-
1940
- 1940-03-27 US US326140A patent/US2330622A/en not_active Expired - Lifetime
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2456151A (en) * | 1943-03-29 | 1948-12-14 | Curtiss Wright Corp | Aircraft engine cooling system |
US2425088A (en) * | 1943-09-13 | 1947-08-05 | Curtiss Wright Corp | Fan blade and mounting means therefor |
US2424839A (en) * | 1943-09-21 | 1947-07-29 | B F Sturtevant Co | Spin vanes control device for cooling fans in aircraft engines |
US2476643A (en) * | 1944-07-01 | 1949-07-19 | United Aircraft Corp | By-pass system for cooling fans |
US2427166A (en) * | 1945-01-22 | 1947-09-09 | Gen Motors Corp | Propeller blade fairing |
US2580789A (en) * | 1945-11-05 | 1952-01-01 | United Aircraft Corp | Adjustable propeller cuff |
US2529103A (en) * | 1946-02-13 | 1950-11-07 | Curtiss Wright Corp | Spinner deicing system |
US2605851A (en) * | 1946-11-30 | 1952-08-05 | Chrysler Corp | Air intake for aircraft turbopropeller power plant |
US2913055A (en) * | 1950-09-01 | 1959-11-17 | Thomas E Quick | Propulsion device |
US3279415A (en) * | 1965-02-25 | 1966-10-18 | Kiekhaefer Corp | Marine propeller for discharging engine exhaust through the propeller hub |
US20040179941A1 (en) * | 2003-02-10 | 2004-09-16 | Dimitrie Negulescu | Turboprop engine with co-rotating two-stage high-performance propeller |
WO2007001372A2 (en) * | 2004-09-17 | 2007-01-04 | Aurora Flight Sciences | Ducted spinner for engine cooling |
US20060102780A1 (en) * | 2004-09-17 | 2006-05-18 | Robert Parks | Ducted spinner for engine cooling |
US20060248873A1 (en) * | 2004-09-17 | 2006-11-09 | Robert Parks | Vibration isolation engine mount system and method for ducted fans |
US20060065776A1 (en) * | 2004-09-17 | 2006-03-30 | Robert Parks | System and method for controlling a roll rate of a torsionally-disconnected freewing aircraft |
US20070221783A1 (en) * | 2004-09-17 | 2007-09-27 | Robert Parks | Adaptive landing gear |
US7441724B2 (en) | 2004-09-17 | 2008-10-28 | Aurora Flight Sciences Corporation | System and method for controlling a roll rate of a torsionally-disconnected freewing aircraft |
WO2007001372A3 (en) * | 2004-09-17 | 2009-04-23 | Aurora Flight Sciences | Ducted spinner for engine cooling |
US7559191B2 (en) | 2004-09-17 | 2009-07-14 | Aurora Flight Sciences Corporation | Ducted spinner for engine cooling |
US8001764B2 (en) | 2004-09-17 | 2011-08-23 | Aurora Flight Sciences Corporation | Vibration isolation engine mount system and method for ducted fans |
US8667775B1 (en) * | 2009-08-05 | 2014-03-11 | The Boeing Company | Reverse flow engine core having a ducted fan with integrated secondary flow blades |
US20180347463A1 (en) * | 2013-04-03 | 2018-12-06 | United Technologies Corporation | Gas turbine engine de-icing system |
US10815884B2 (en) * | 2013-04-03 | 2020-10-27 | Raytheon Technologies Corporation | Gas turbine engine de-icing system |
US20180045138A1 (en) * | 2015-02-09 | 2018-02-15 | United Technologies Corporation | Nose cone assembly and method of circulating air in a gas turbine engine |
US9920708B2 (en) * | 2015-02-09 | 2018-03-20 | United Technologies Corporation | Nose cone assembly and method of circulating air in a gas turbine engine |
US20160298540A1 (en) * | 2015-04-13 | 2016-10-13 | United Technologies Corporation | Nose cone assembly and method of circulating air in a gas turbine engine |
US10060350B2 (en) * | 2015-04-13 | 2018-08-28 | United Technologies Corporation | Nose cone assembly and method of circulating air in a gas turbine engine |
US20170122207A1 (en) * | 2015-11-04 | 2017-05-04 | United Technologies Corporation | Engine with nose cone heat exchanger and radially outer discharge |
US10215096B2 (en) * | 2015-11-04 | 2019-02-26 | United Technologies Corporation | Engine with nose cone heat exchanger and radially outer discharge |
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