US2078116A - Aircraft engine heater - Google Patents

Aircraft engine heater Download PDF

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Publication number
US2078116A
US2078116A US77876A US7787636A US2078116A US 2078116 A US2078116 A US 2078116A US 77876 A US77876 A US 77876A US 7787636 A US7787636 A US 7787636A US 2078116 A US2078116 A US 2078116A
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United States
Prior art keywords
aircraft engine
envelope
engine heater
engine
plate
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Expired - Lifetime
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US77876A
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Arndt Edwin James
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Individual
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Individual
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Priority to US77876A priority Critical patent/US2078116A/en
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Publication of US2078116A publication Critical patent/US2078116A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
    • F02N19/00—Starting aids for combustion engines, not otherwise provided for
    • F02N19/02—Aiding engine start by thermal means, e.g. using lighted wicks
    • F02N19/04—Aiding engine start by thermal means, e.g. using lighted wicks by heating of fluids used in engines
    • F02N19/10—Aiding engine start by thermal means, e.g. using lighted wicks by heating of fluids used in engines by heating of engine coolants

Definitions

  • 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
  • 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.
  • Figure 1 is a side elevation of an airplane urel.
  • 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.
  • 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
  • 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.
  • 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.
  • 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
  • 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

Description

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.
- JAMES ARNDT.
US77876A 1936-05-04 1936-05-04 Aircraft engine heater Expired - Lifetime US2078116A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US77876A US2078116A (en) 1936-05-04 1936-05-04 Aircraft engine heater

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US77876A US2078116A (en) 1936-05-04 1936-05-04 Aircraft engine heater

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US2078116A true US2078116A (en) 1937-04-20

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2417636A (en) * 1943-02-08 1947-03-18 New Castle Products Engine heating cover system
US2419626A (en) * 1943-01-29 1947-04-29 Petroleum Heat & Power Co Heater
US2646028A (en) * 1950-09-29 1953-07-21 Vapor Heating Corp Standby hot water heater for buses
US2655090A (en) * 1949-08-25 1953-10-13 Cons Vultee Aircraft Corp Thermal shroud for engine mounts
US4445469A (en) * 1982-04-05 1984-05-01 Louis Suhayda Engine heater
US4815426A (en) * 1987-02-26 1989-03-28 Henschel Paul S Engine heater, small, portable
US5381987A (en) * 1994-05-31 1995-01-17 Carns; William A. Utility vehicle for towing and servicing aircraft

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2419626A (en) * 1943-01-29 1947-04-29 Petroleum Heat & Power Co Heater
US2417636A (en) * 1943-02-08 1947-03-18 New Castle Products Engine heating cover system
US2655090A (en) * 1949-08-25 1953-10-13 Cons Vultee Aircraft Corp Thermal shroud for engine mounts
US2646028A (en) * 1950-09-29 1953-07-21 Vapor Heating Corp Standby hot water heater for buses
US4445469A (en) * 1982-04-05 1984-05-01 Louis Suhayda Engine heater
US4815426A (en) * 1987-02-26 1989-03-28 Henschel Paul S Engine heater, small, portable
US5381987A (en) * 1994-05-31 1995-01-17 Carns; William A. Utility vehicle for towing and servicing aircraft

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