US2019270516A1PendingUtilityA1

Propulsion Systems for Rotorcraft

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Assignee: BELL HELICOPTER TEXTRON INCPriority: Mar 1, 2018Filed: Mar 1, 2018Published: Sep 5, 2019
Est. expiryMar 1, 2038(~11.6 yrs left)· nominal 20-yr term from priority
Inventors:Eric A. SinusasErik John OlthetenCarlos Alexander Fenny
B64C 27/12B64C 27/82B64C 2027/8281B64C 27/00B64C 27/20B64C 27/08
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Claims

Abstract

A propulsion system for a rotorcraft includes a first fan assembly including a plurality of first fan blades, a second fan assembly including a plurality of second fan blades and a drive system adapted to provide torque to the first and second fan blades. The first fan blades have a larger rotational inertia than the second fan blades. The second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.

Claims

exact text as granted — not AI-modified
What is claimed is: 
     
         1 . A propulsion system for a rotorcraft comprising:
 a first fan assembly including a plurality of first fan blades;   a second fan assembly including a plurality of second fan blades; and   a drive system adapted to provide torque to the first and second fan blades;   wherein, the first fan blades have a larger rotational inertia than the second fan blades; and   wherein, the second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.   
     
     
         2 . The propulsion system as recited in  claim 1  wherein the first and second fan blades further comprise fixed pitch fan blades. 
     
     
         3 . The propulsion system as recited in  claim 1  wherein the first fan blades are longer than the second fan blades. 
     
     
         4 . The propulsion system as recited in  claim 1  wherein the first fan blades are formed from a different material than the second fan blades. 
     
     
         5 . The propulsion system as recited in  claim 1  wherein the plurality of first fan blades include a larger number of fan blades than the plurality of second fan blades. 
     
     
         6 . The propulsion system as recited in  claim 1  wherein the first fan blades are wider than the second fan blades. 
     
     
         7 . The propulsion system as recited in  claim 1  wherein the first fan blades further comprise a circumferential tip ring. 
     
     
         8 . The propulsion system as recited in  claim 1  wherein at least one of the first or second fan assemblies further comprise a shrouded fan assembly. 
     
     
         9 . The propulsion system as recited in  claim 1  wherein at least one of the first or second fan assemblies further comprise an open fan assembly. 
     
     
         10 . The propulsion system as recited in  claim 1  wherein the first fan blades are adapted to provide a larger maximum thrust than the second fan blades. 
     
     
         11 . The propulsion system as recited in  claim 1  wherein the drive system further comprises an electric motor. 
     
     
         12 . The propulsion system as recited in  claim 1  wherein the drive system further comprises a hydraulic motor. 
     
     
         13 . The propulsion system as recited in  claim 1  wherein the drive system further comprises a variable speed motor. 
     
     
         14 . A rotorcraft comprising:
 a fuselage; and   a propulsion system coupled to the fuselage, the propulsion system comprising:   a first fan assembly including a plurality of first fan blades;   a second fan assembly including a plurality of second fan blades; and   a drive system adapted to provide torque to the first and second fan blades;   wherein, the first fan blades have a larger rotational inertia than the second fan blades; and   wherein, the second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.   
     
     
         15 . The rotorcraft as recited in  claim 14  wherein the second fan assembly further comprises a plurality of second fan assemblies. 
     
     
         16 . The rotorcraft as recited in  claim 15  wherein the plurality of second fan assemblies further comprise at least four second fan assemblies. 
     
     
         17 . The rotorcraft as recited in  claim 15  wherein the first fan assembly further comprises a central fan assembly including a mast; and
 wherein the second fan assemblies are radially symmetric about the mast of the central fan assembly. 
 
     
     
         18 . The rotorcraft as recited in  claim 17  wherein the central fan assembly forms a rotor disk and the second fan assemblies are disposed outboard of the rotor disk of the central fan assembly. 
     
     
         19 . The rotorcraft as recited in  claim 17  wherein the central fan assembly forms a rotor disk and the second fan assemblies are disposed underneath the rotor disk of the central fan assembly. 
     
     
         20 . The rotorcraft as recited in  claim 17  wherein the first fan blades of the central fan assembly further comprise variable pitch fan blades; and
 wherein the second fan blades of the second fan assemblies further comprise fixed pitch fan blades.

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