Piston type aircraft engine

Abstract

A propulsion assembly for propelling an aircraft is disclosed. The assembly includes a four stroke internal combustion engine, a propeller shaft that is operatively connected to the engine, and an electronic control unit that is connected to the engine and is configured to monitor and control at least one operating parameter of the engine. The engine includes two to twelve cylinders having a total displacement of less than 19.6 liters, and a crankshaft that is operatively connected to the cylinders. The crankshaft rotates at a speed of at least 3,000 rpm when the engine is operating under normal conditions. The engine also includes a closed loop liquid cooling system and a fuel injection system. The engine has a total power output of 140 to 600 hp, and a total wet installed weight of less than 1.1 kg/hp. The engine meets current RTCA DO-160d, RTCA DO-178b, and US FAA FAR33 guidelines.

1 . A propulsion assembly suitable for placement in an aircraft for propelling the aircraft, the assembly comprising: 
 (A) a four stroke internal combustion engine, the engine comprising 
 (1) one to twelve cylinders having a total displacement of less than about 19.6 liters;  
 (2) a crankshaft operatively connected to the cylinders, the crankshaft rotating at a speed of at least 3000 revolutions per minute when the engine is operating under normal conditions;  
 (3) a closed loop cooling system constructed and arranged to provide cooling at least to the cylinders; and  
 (4) a fuel injection system operatively connected to the cylinders to provide fuel for combustion,  
 the engine having a total power output of about 140 to about 600 horsepower, and a total wet installed weight of less than about 1.1 kilogram per horsepower produced;  
   (B) a propeller shaft operatively connected to the engine, the propeller shaft rotating at a speed of about 100 to about 2999 revolutions per minute when the engine is operating under normal conditions; and    (C) an electronic control unit, the electronic control unit electrically connected to the engine and configured to monitor and control at least one operating parameter of the engine,    wherein the propulsion assembly satisfies RTCA DO-160d, RTCA DO-178b, and US FAA FAR 33 guidelines.    
   
   
       2 . The assembly of  claim 1 , wherein the engine comprises four to twelve cylinders.  
   
   
       3 . The assembly of  claim 2 , wherein the engine comprises four to eight cylinders.  
   
   
       4 . The assembly of  claim 3 , wherein the engine comprises six cylinders.  
   
   
       5 . The assembly of  claim 1 , wherein the total displacement of the cylinders is about 1.4 to about 10 liters.  
   
   
       6 . The assembly of  claim 5 , wherein the total displacement of the cylinders is about 2.2 to about 8 liters.  
   
   
       7 . The assembly of  claim 6 , wherein the total displacement of the cylinders is about 2.5 to about 5.4 liters.  
   
   
       8 . The assembly of  claim 7 , wherein the total displacement of the cylinders is about 3.1 liters.  
   
   
       9 . The assembly of  claim 1 , wherein the speed of the crankshaft is about 3000 to about 6000 revolutions per minute when the engine is operating under normal conditions.  
   
   
       10 . The assembly of  claim 9 , wherein the speed of the crankshaft is about 4000 to about 6000 revolutions per minute when the engine is operating under normal conditions.  
   
   
       11 . The assembly of  claim 10 , wherein the speed of the crankshaft is about 4500 to about 5500 revolutions per minute when the engine is operating under normal conditions.  
   
   
       12 . The assembly of  claim 11 , wherein the speed of the crankshaft is about 4800 revolutions per minute when the engine is operating under normal conditions.  
   
   
       13 . The assembly of  claim 1 , wherein the total engine output is about 150 to about 500 horsepower.  
   
   
       14 . The assembly of  claim 13 , wherein the total engine output is about 160 to about 400 horsepower.  
   
   
       15 . The assembly of  claim 14 , wherein the total engine output is about 170 to about 375 horsepower.  
   
   
       16 . The assembly of  claim 15 , wherein the total engine output is about 180 to about 350 horsepower.  
   
   
       17 . The assembly of  claim 16 , wherein the total engine output is about 220 horsepower.  
   
   
       18 . The assembly of  claim 16 , wherein the total engine output is about 300 horsepower.  
   
   
       19 . The assembly of  claim 1 , wherein the total wet installed weight of the engine is less than about 1.0 kilogram per horsepower.  
   
   
       20 . The assembly of  claim 19 , wherein the total wet installed weight of the engine is less than about 0.9 kilogram per horsepower.  
   
   
       21 . The assembly of  claim 1 , wherein the speed of the propeller shaft is about 1900 to about 2400 revolutions per minute.  
   
   
       22 . The assembly of  claim 21 , wherein the speed of the propeller shaft is about 2000 to about 2200 revolutions per minute.  
   
   
       23 . The assembly of  claim 22 , wherein the speed of the propeller shaft is about 2000 revolutions per minute.  
   
   
       24 . The assembly of  claim 1 , further comprising a turbocharger.  
   
   
       25 . The assembly of  claim 24 , further comprising an intercooler operatively connected to the turbocharger.  
   
   
       26 . The assembly of  claim 1 , wherein opposing cylinders are disposed in a V configuration.  
   
   
       27 . The assembly of  claim 26 , wherein an angle between the opposing cylinders is about 120°.  
   
   
       28 . The assembly of  claim 1 , wherein the at least one operating parameter of the engine comprises at least one of the speed of the crankshaft or an air-to-fuel ratio in the cylinders.  
   
   
       29 . The assembly of  claim 28 , wherein the electronic control unit further monitors and controls a pitch of the propeller.  
   
   
       30 . The assembly of  claim 1 , wherein the engine comprises aluminum.  
   
   
       31 . The assembly of  claim 1 , wherein the fuel is selected from the group consisting of unleaded fuel and leaded fuel.  
   
   
       32 . The assembly of  claim 1 , wherein the fuel is unleaded fuel suitable for use in an automobile.  
   
   
       33 . The assembly of  claim 1 , further comprising a gear box operatively connected to the crankshaft and the propeller shaft, wherein the gear box is configured to transmit the speed of the crankshaft to the propeller shaft such that the speed of the propeller shaft is less than the speed of the crankshaft.  
   
   
       34 . A propulsion assembly suitable for placement in an aircraft for propelling the aircraft, the assembly comprising: 
 (A) a four stroke internal combustion engine, the engine comprising 
 (1) four to eight cylinders disposed in a V configuration, the cylinders having a total displacement of about 2.5 to about 5.4 liters;  
 (2) a crankshaft operatively connected to the cylinders, the crankshaft rotating at a speed of about 4500 to about 5500 revolutions per minute when the engine is operating under normal conditions;  
 (3) a closed loop cooling system constructed and arranged to provide cooling at least to the cylinders; and  
 (4) a fuel injection system operatively connected to the cylinders to provide fuel for combustion,  
 the engine having a total power output of about 180 to about 350 horsepower, and a total wet installed weight of less than about 1.0 kilogram per horsepower produced;  
   (B) a gear box operatively connected to the crankshaft;    (C) a propeller shaft operatively connected to the gear box, the propeller shaft rotating at a speed of about 2000 to about 2200 revolutions per minute when the engine is operating under normal conditions; and    (D) an electronic control unit, the electronic control unit electrically connected to the engine and configured to monitor and control at least one operating parameter of the engine,    wherein the propulsion assembly satisfies RTCA DO-160d, RTCA DO-178b, and US FAA FAR 33 guidelines.    
   
   
       35 . The assembly of  claim 34 , wherein an angle between the opposing cylinders is about 120°.  
   
   
       36 . The assembly of  claim 34 , wherein the fuel is unleaded fuel suitable for use in an automobile.  
   
   
       37 . A propulsion assembly suitable for placement in an aircraft for propelling the aircraft, the assembly comprising: 
 (A) an internal combustion engine, the engine comprising 
 (1) one to twelve cylinders;  
 (2) a crankshaft operatively connected to the cylinders; and  
 (3) an internal generator operatively connected to the crankshaft;  
   (B) a propeller shaft operatively connected to the engine; and    (C) an electronic control unit connected to the engine and configured to monitor and control at least one operating parameter of the engine,    wherein the internal generator is connected to the electronic control unit and provides power to the electronic control unit and to the engine when the crankshaft is rotating, and    wherein the propulsion assembly satisfies RTCA DO-160d, RTCA DO-178b, and US FAA FAR 33 guidelines.    
   
   
       38 . The assembly of  claim 37 , wherein the internal generator is mounted to a first end of the crankshaft.  
   
   
       39 . The assembly of  claim 38 , further comprising a second internal generator, wherein the second internal generator is mounted to a second end of the crankshaft.  
   
   
       40 . The assembly of  claim 37 , wherein the crankshaft is operatively connected to two alternators.  
   
   
       41 . The assembly of  claim 37 , wherein the internal generator provides power to all electrical equipment required to operate the engine.