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Publication numberUS2078116 A
Publication typeGrant
Publication dateApr 20, 1937
Filing dateMay 4, 1936
Priority dateMay 4, 1936
Publication numberUS 2078116 A, US 2078116A, US-A-2078116, US2078116 A, US2078116A
InventorsArndt Edwin James
Original AssigneeArndt Edwin James
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Aircraft engine heater
US 2078116 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

April 20, 1937. E. J. ARNDT AIRCRAFT ENGINE HEATER Filed May 4, 1936 2 Sheets-Sheet 1 22mm JArmZi,

ATTORNEY WITNESS April 20, 1937.

E. J. ARNDT AIRCRAFT ENGINE HEATER Filed May 4, 1956' 2 Sheets-Sheet 2 Edwin Jflrzzdt,

WITNESS ATTORNEYS from, will positively prevent retrograde move-' Patented Apr. 20, 1937 PATENT OFFICE AIRCRAFT ENGINE HEATER 5' Edwin James Amdt, Irvington, N. J. Application- May 4, 1936, Serial No. 77,876

1 Claim.

This invention relates to aircraft engine heaters and has for an object to provide an envelope within which the engine may be received, the envelope having a heated chamber associated therewith and separated therefrom by a plate through which plate heated gases may be conducted into the envelope forv warming up the engine, while at the same time the plate being imperforate except for the pipe openings therement of the gas and oil fumes backing into the heated chamber.

A further object is to provide a deviceof this character which may be made of light flexible material and may be disassembled, folded and placed in a compact package for stowage on I the airplane.

with the above and, other objects in view the invention consists of certain novel details of construction and combinations of parts hereinafter fully described and claimed, it being understood that various modifications may be resorted to within the scope of the appended claim without departing from the spirit or sacrificing any of the advantages of the invention.

In the 'accompanying drawings forming part of this specification,

Figure 1 is a side elevation of an airplane urel.

Referring now to the drawings in which like characters of reference designate similar parts in the various views, the aircraft engine heater is shown to comprise a front piece III of canvas lined on the inner face with a pliable asbestos piece II. The front piece is circular and is pro-- vided with a central opening I2 to receive the propeller hub l3 and is provided with a radial opening closed by a 'zlpper ll to permit the front piece being appliedto the hub in front of the .engine.

A cylindrical sheet l5 of canvas, lined with a pliable asbestos sheet I6, forms an envelope ing of the engine.

together with the front piece ID to completely enclose the engine I! of the airplane i 8. The front edge of the cylindrical sheet I5 is connected by azipper [9 to the edge of the front piece ID. V

The side edges of the cylindrical sheet i5 are connected by a zipper 20. The rear corners of the cylindrical sheet are provided with strap sections 2| and a buckle 22. I

A plate 23, preferably formed of aluminum is secured to the lower end of thefront piece and is provided with a plurality of openings 24. Pipes 25 communicate with theopenings and are secured to the front piece by straps 26 or other suitable means. A burner housing 21 is secured to the plate and is provided with a damper 28. The housing is preferably formed of aluminum and is spaced outside with a can- Vas sheet 29 and is-lined inside with an asbestos sheet 30.

A burner 3| of the Bunsen type is secured in the bottom of the housing and is provided with a control valve 32. A flexible tube 33 is connected to the burner below the valve and is connected at the free end to a tank 34 which preferably is filled with natural gas under compression. As natural gas is high in heat value a small tank of gas will supply the burner for heating the airplane motor a plurality of times.

A door 35 closes a sight opening 36 in the wall of the burner housing, the door being hinged as shown at 31 to the wall of the housing and being equipped with an isinglass pane 38 through which the burner may be viewed while regulating the height of the flame as will be understood.

In operation the cylindrical envelope with its circular front wall and rear open end, may be applied to the airplane motor to envelop the same .throughout'wher'eupon the zipper 20 may be closed and the strap sections 2| may no be buckled together to hold the device firmy in place. Heated air and products of combustion, being relatively light, will r'isethrough the pipes 26 and heat the enclosure within the envelope so that the lubricating oil and the engine parts will be warmed preparatory to easy starn By virtue of the plate 23 being imperforate the gas and oil-fumes cannot escape in a retrograde direction hacking into the heating chamber.

The device may be compactly stored when removed from applied position by simply removing it from the engine, foldingthe envelope 10 an aircraft engine, said envelope having an opening in the lower front portion thereof, an

*apertured plate secured in said opening, distributing pipes extending from the apertures of the plate to various points within and adjacent the front portion of the envelope, said pipes being fastened to the front wall of the envelope, a burner housing suspended from said plate, and a burner within the housing for delivery of heated gases to said pipes.


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2417636 *Feb 8, 1943Mar 18, 1947New Castle ProductsEngine heating cover system
US2419626 *Jan 29, 1943Apr 29, 1947Petroleum Heat & Power CoHeater
US2646028 *Sep 29, 1950Jul 21, 1953Vapor Heating CorpStandby hot water heater for buses
US2655090 *Aug 25, 1949Oct 13, 1953Cons Vultee Aircraft CorpThermal shroud for engine mounts
US4445469 *Apr 5, 1982May 1, 1984Louis SuhaydaEngine heater
US4815426 *Feb 26, 1987Mar 28, 1989Henschel Paul SEngine heater, small, portable
US5381987 *May 31, 1994Jan 17, 1995Carns; William A.Utility vehicle for towing and servicing aircraft
U.S. Classification126/93, 123/543, 432/219, 123/142.50R, 123/41.34, 135/92, 244/59, 244/53.00R, 123/179.21, 237/50
International ClassificationF02N19/10
Cooperative ClassificationF02N19/10
European ClassificationF02N19/10