Aircraft with ram air turbine disk with generator having blade shroud ring integrated magnets

Abstract

The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

What is claimed is: 
     
         1 . An aircraft comprising
 a propulsion system configured to produce thrust for driving the aircraft during operation,   an accessory system electrically de-coupled from the propulsion system so as not to directly draw power from the propulsion system, and   a ram air turbine power system electrically coupled to the accessory system to provide energy for use by the accessory system, the ram air turbine power system including
 a turbine case that extends around a central axis, 
 a turbine rotor mounted for rotation about the central axis with an outer diameter in confronting relation with the turbine case, an inner diameter spaced radially inward of the outer diameter, and airfoils arranged between the outer diameter and the inner diameter, wherein each airfoil extends from a base radially outward to a tip thereof, and 
 an accessory generator including a stator and a plurality of magnets coupled with each of the airfoils, the stator being coupled with the turbine case and axially aligned with the airfoils of the turbine rotor, the stator including a plurality of stator windings, and the plurality of magnets being located within the tip of each of the airfoils so that, upon rotation of the turbine rotor, electrical power is generated for use by the accessory system. 
   
     
     
         2 . The aircraft of  claim 1 , wherein each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil and the plurality of magnets are located axially on a mid-chord of the chord of each airfoil. 
     
     
         3 . The aircraft of  claim 1 , wherein each of the airfoils includes a body and the tip which provide a leading edge, a pressure side, a suction side, and a trailing edge of the airfoil, and wherein the body of each of the airfoils is formed to define a cavity therein, and the airfoil further includes a corrugation sidewall located in the cavity and extending axially from the leading edge to the trailing edge and extending alternatingly between the pressure side and the suction side. 
     
     
         4 . The aircraft of  claim 1 , wherein each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil and the plurality of magnets extends axially along a length of the chord between the leading edge of the trailing edge of the airfoil. 
     
     
         5 . The aircraft of  claim 1 , wherein the tip of each of the airfoils includes a skin located radially outward of and extending axially along the plurality of magnets to block radial movement of the plurality of magnets relative to the central axis. 
     
     
         6 . The aircraft of  claim 5 , wherein each of the airfoils further include a metallic strip coupled to at least one magnet of the plurality of magnets and located radially between the plurality of magnets and the base of the airfoil. 
     
     
         7 . The aircraft of  claim 1 , wherein the ram air turbine power system further includes a plurality of turbine inlet guide vanes configured to redirect air moving into the turbine case for interaction with the airfoils of the turbine rotor, the turbine inlet guide vanes are located axially forward of the turbine rotor, and the accessory generator includes power off-take wires that extend from the stator windings radially inward along the turbine inlet guide vanes. 
     
     
         8 . The aircraft of  claim 7 , wherein the power off-take wires extend along a leading edge of the plurality of turbine inlet guide vanes so that heat from the power off-take wires is supplied to the plurality of turbine inlet guide vanes. 
     
     
         9 . The aircraft of  claim 7 , wherein each of the plurality of turbine inlet guide vanes are formed to define radially extending passages therethrough and the ram air turbine power system further includes a cooling system that includes cooling fluid conduits that extend radially through the passages formed in the plurality of turbine inlet guide vanes. 
     
     
         10 . The aircraft of  claim 1 , wherein the plurality of magnets are arranged so that magnetic directionality is selected such that the plurality of magnets forms a Halbach array configured to provide managed power density. 
     
     
         11 . The aircraft of  claim 1 , wherein the ram air turbine power system is housed in a pod having a turbine inlet configured to be selectively opened and closed to modulate air flow allowed into the turbine case for interaction with the turbine rotor so as to regulate speed of the turbine rotor and thereby control power output of the accessory generator. 
     
     
         12 . The aircraft of  claim 11 , wherein the pod has a turbine outlet configured to be selectively opened and closed to modulate air flow allowed out of the turbine case so as to regulate speed of the turbine rotor and thereby control power output of the accessory generator. 
     
     
         13 . An independently-powered unit configured to be coupled to an aircraft, the unit comprising
 a pod with attachment points for coupling the unit to the aircraft and defining an interior space,   an accessory system mounted in the interior space of the pod, and   a ram air turbine power system mounted in the interior space of the pod and electrically coupled to the accessory system to provide energy for use by the accessory system,   wherein the ram air turbine power system includes a turbine case that extends around a central axis, a turbine rotor mounted for rotation about the central axis and having a plurality of airfoils that extend from a base radially outward to a tip thereof, and an accessory generator including a stator and a plurality of magnets coupled with each of the plurality of airfoils, the stator including a plurality of stator windings and the plurality of magnets coupled discretely with the tip of each airfoil of the plurality of airfoils so that, upon rotation of the turbine rotor, electrical power is generated for use by the accessory system.   
     
     
         14 . The independently-powered unit of  claim 13 , wherein each of the airfoils includes a body and the tip which provide a leading edge, a pressure side, a suction side, and a trailing edge, and wherein the body of each of the airfoils is formed to define a cavity and a corrugation sidewall located in the cavity and extending axially from the leading edge to the trailing edge. 
     
     
         15 . The independently-powered unit of  claim 13 , wherein each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil and the plurality of magnets is located axially on a mid-chord of the chord of the airfoil. 
     
     
         16 . The independently-powered unit of  claim 13 , wherein the plurality of magnets coupled with each airfoil extends circumferentially discretely only partway around the central axis. 
     
     
         17 . The independently-powered unit of  claim 13 , wherein each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil and the plurality of magnets extends axially along a length of the chord between the leading edge of the trailing edge of the airfoil. 
     
     
         18 . The independently-powered unit of  claim 13 , wherein each of the airfoils further include a skin that forms the tip of each airfoil to block radial movement of the plurality of magnets relative to the central axis. 
     
     
         19 . The independently-powered unit of  claim 18 , wherein each of the airfoils further include a metallic strip coupled to at least one magnet of the plurality of magnets and is located radially between the plurality of magnets and the base of the airfoil. 
     
     
         20 . The independently-powered unit of  claim 13 , wherein the pod includes a turbine inlet configured to be selectively opened and closed to modulate air flow allowed into the turbine case for interaction with the turbine rotor so as to regulate speed of the turbine rotor and thereby control power output of the accessory generator, and wherein the pod includes a turbine outlet configured to be selectively opened and closed to modulate air flow allowed out of the turbine case so as to regulate speed of the turbine rotor and thereby control power output of the accessory generator.