US1553854A - Internal-combustion engine for aircraft - Google Patents

Internal-combustion engine for aircraft Download PDF

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Publication number
US1553854A
US1553854A US757681A US75768124A US1553854A US 1553854 A US1553854 A US 1553854A US 757681 A US757681 A US 757681A US 75768124 A US75768124 A US 75768124A US 1553854 A US1553854 A US 1553854A
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United States
Prior art keywords
aircraft
combustion engine
internal
gun
engine
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Expired - Lifetime
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US757681A
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Fornaca Guido
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Individual
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Priority to US757681A priority Critical patent/US1553854A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B33/00—Engines characterised by provision of pumps for charging or scavenging
    • F02B33/32—Engines with pumps other than of reciprocating-piston type
    • F02B33/34—Engines with pumps other than of reciprocating-piston type with rotary pumps
    • F02B33/36—Engines with pumps other than of reciprocating-piston type with rotary pumps of positive-displacement type
    • F02B33/38—Engines with pumps other than of reciprocating-piston type with rotary pumps of positive-displacement type of Roots type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B67/00—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
    • F02B67/10—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for of charging or scavenging apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B3/00—Engines characterised by air compression and subsequent fuel addition
    • F02B3/06—Engines characterised by air compression and subsequent fuel addition with compression ignition

Definitions

  • the object yof, this invention is to provide an .improved superfeed internal combustion engine for aircraft, ofthe kind having the forced feed compressor arranged l between the engine cylinders, a propeller sef cured on 'ahollow counter shaft, and a'gun adapted to fire through said shaft.
  • the principal stationary parts'v such as the engine casing, the crank chamber, parts of the cylinders, and the'compressor casing, are cast in a single piece.
  • the casting includes the engine casing, the propeller casing, and also parts of the aforesaid' gun. f I Provision may be made for circulating the air drawn in by the forced feed compressor round the end of the gun barrel,V
  • Fig. l is a vertical transverse section of the'engine on the lineA-B of Fig. 2 and Fig. 2 is a vertical section on the line -D vof Fig. 1.
  • the reference 1 denotes the engine casing cast in one. with the" crank chamber 2, the cylinderwater jackets 3', the
  • compressor casing 4 and the recoil case 13 of a-gun, which may be asmachine gun or automatic gun.
  • the inlet pipes 10 of the compressor 4 envelop the ends of the hollow counter shaft or propeller shaft 11 and the barrel 12 of the gun, which is mounted coaxial'with said shaft, in order to cool these parts'. In some cases, however, this feature may be omitted;
  • a superfeedr ⁇ internal combustion engine for aircraft having the forced feed compressor arranged between the cylinders, a propeller secured on a hollow counter shaft, and a gun ladapted to fire through said shaft, with the' characteristic vfeaturel that the principal stationary parts such as the engine casing, the cylinder jackets, the compressor casing, andthe re-l GUIDO FORNACA.4

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)

Description

sept. 15, 1925 1,553,854
G. FORNACA l INTERNAL COMBUSTION ENGINE FOR AIRCRAFT vFile Dec 25. 1924 Patented Sept. 15,1 1925. i
' UNITED STATES PATENT orner-1.
, como scannen, or moana-HALS?.
. INTERNAL-COMBUSTION ENGINE FOR AIRCRAFT.
- Application led December 28, 1924. Serial No. '2157,881.`
Toallwlomvtmay concern:
Be it known that., I, Grumo FonNAoA, a subject of the King of Italy, resident of Turin, in the Kingdom of Italy, have invented certain new and useful Improvements in Internal-Combustion. Engines for Aircraft; and I do hereby declare the following to be a full, clear, and exact description of the invention, such as will enable others skilled in the art to .which it u appertains to make and use the same, reference being had to the accompan ing drawings, and to letters' or figures o reference marked thereon, which form a part of this 1. specification.
The object yof, this invention is to provide an .improved superfeed internal combustion engine for aircraft, ofthe kind having the forced feed compressor arranged l between the engine cylinders, a propeller sef cured on 'ahollow counter shaft, and a'gun adapted to fire through said shaft. A
In accordance with the invention the principal stationary parts'v such as the engine casing, the crank chamber, parts of the cylinders, and the'compressor casing, are cast in a single piece. I
Preferably, the casting includes the engine casing, the propeller casing, and also parts of the aforesaid' gun. f I Provision may be made for circulating the air drawn in by the forced feed compressor round the end of the gun barrel,V
and also, if desired', round the end of the counter shaft or propeller shaft, through which the gun tires, in order to cool these parts. I
The accompanying drawing shows, by way of example, one form'of the improved engine. i v
Fig. l is a vertical transverse section of the'engine on the lineA-B of Fig. 2 and Fig. 2 is a vertical section on the line -D vof Fig. 1.
On the drawing, the reference 1 denotes the engine casing cast in one. with the" crank chamber 2, the cylinderwater jackets 3', the
compressor casing 4, and the recoil case 13 of a-gun, which may be asmachine gun or automatic gun.
In this casting are inserted, after the necessary machining operations, the cylinders 6 and heads 7 and 8, which latter assist in supporting the crank shaft 9;
The inlet pipes 10 of the compressor 4 envelop the ends of the hollow counter shaft or propeller shaft 11 and the barrel 12 of the gun, which is mounted coaxial'with said shaft, in order to cool these parts'. In some cases, however, this feature may be omitted;
lalso the casting .containing the stationary parts may be less completi, the cylinders and the crank chamber, for, example, being separate. A 4 i' A WhatIclaimisz I y l1. A superfeedr` internal combustion engine for aircraft, ofthe kind having the forced feed compressor arranged between the cylinders, a propeller secured on a hollow counter shaft, and a gun ladapted to fire through said shaft, with the' characteristic vfeaturel that the principal stationary parts such as the engine casing, the cylinder jackets, the compressor casing, andthe re-l GUIDO FORNACA.4
US757681A 1924-12-23 1924-12-23 Internal-combustion engine for aircraft Expired - Lifetime US1553854A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US757681A US1553854A (en) 1924-12-23 1924-12-23 Internal-combustion engine for aircraft

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US757681A US1553854A (en) 1924-12-23 1924-12-23 Internal-combustion engine for aircraft

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US1553854A true US1553854A (en) 1925-09-15

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442838A (en) * 1944-06-08 1948-06-08 Chrysler Corp Drive construction
US2442917A (en) * 1942-08-17 1948-06-08 Chrysler Corp Supporting structure for bearings for piston-connected shafts
US2483941A (en) * 1945-02-19 1949-10-04 Steel Products Eng Co Braking system
US2551307A (en) * 1944-10-14 1951-05-01 Frank B Yingling Turbocharged two-cycle engine with liquid cooled exhaust ducts
US5513601A (en) * 1994-03-01 1996-05-07 Benson; Robert A. Aircraft engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442917A (en) * 1942-08-17 1948-06-08 Chrysler Corp Supporting structure for bearings for piston-connected shafts
US2442838A (en) * 1944-06-08 1948-06-08 Chrysler Corp Drive construction
US2551307A (en) * 1944-10-14 1951-05-01 Frank B Yingling Turbocharged two-cycle engine with liquid cooled exhaust ducts
US2483941A (en) * 1945-02-19 1949-10-04 Steel Products Eng Co Braking system
US5513601A (en) * 1994-03-01 1996-05-07 Benson; Robert A. Aircraft engine

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