AIRCRAFT WITH RAM AIR TURBINE DISK WITH GENERATOR HAVING BLADE SHROUD RING INTEGRATED MAGNETS
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.
This application is a continuation of, and claims priority to and the benefit of, U.S. patent application Ser. No. 17/702,757, filed 23 Mar. 2022, the disclosure of which is now expressly incorporated herein by reference.
FIELD OF THE DISCLOSUREThe present disclosure relates generally to aircraft accessory power systems, and more specifically to ram air turbines for powering aircraft accessories.
BACKGROUNDAircraft have been fitted with ram air turbines (RATs) configured to generate power from ram pressure derived from the airstream across a moving aircraft. These ram air turbines have been used in emergency situations in the case of primary power source loss to operate critical controls, hydraulics, and/or instrumentation.
Ram air turbines have also been incorporated into independent units or pods included in aircraft. Use of ram air turbines in independent units allows installation onto aircraft without dedicated power supplies from primary electrical systems of the aircraft. Some such independent units have incorporated exposed turbine rotors coupled via shafts to generators to power electronics or to pressurize hydraulics.
Next generation independent units or pods for use with existing or new aircraft continue to demand independent power generation capability to provide flexibility of use. In these aircraft improved packaging and functionality for ram air turbine technology is of significant interest.
SUMMARYThe present disclosure may comprise one or more of the following features and combinations thereof.
According to an illustrative aspect of the present disclosure, an aircraft includes a propulsion system, an accessory system, and a ram air turbine power system. The propulsion system is configured to produce thrust for driving the aircraft during operation. The accessory system is electrically de-coupled from the propulsion system so as not to directly draw power from the propulsion system. The ram air turbine power system is electrically coupled to the accessory system to provide energy for use by the accessory system.
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 an accessory generator configured to generate electrical power for use by the accessory system. The turbine rotor has an outer diameter, an inner diameter, and airfoils. The outer diameter is in confronting relation with the turbine case. The inner diameter is spaced radially inward of the outer diameter. The airfoils are arranged between the outer diameter and the inner diameter. Each airfoil extends from a base radially outward to a tip thereof.
The accessory generator includes a stator and a plurality of magnets coupled with each of the airfoils. The stator is coupled with the turbine case, is axially aligned with the airfoils of the turbine rotor, and includes a plurality of stator windings. The plurality of magnets are 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.
In some embodiments, 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. In some embodiments, 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. The body of each of the airfoils is formed to define a cavity therein. 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.
In some embodiments, each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil. The plurality of magnets extends axially along a length of the chord between the leading edge of the trailing edge of the airfoil.
In some embodiments, 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. In some embodiments, 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.
In some embodiments, 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. The accessory generator includes power off-take wires that extend from the stator windings radially inward along the turbine inlet guide vanes.
In some embodiments, 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. In some embodiments, each of the plurality of turbine inlet guide vanes are formed to define radially extending passages therethrough. 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.
In some embodiments, 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.
In some embodiments, 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. In some embodiments, 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.
According to another illustrative aspect of the disclosure, an independently-powered unit configured to be coupled to an aircraft includes a pod, an accessory system, and a ram air turbine power system. The pod has attachment points for coupling the unit to the aircraft and defining an interior space. The accessory system is mounted in the interior space of the pod. The ram air turbine power system is mounted in the interior space of the pod and is electrically coupled to the accessory system to provide energy for use by the accessory system.
The ram air turbine power system includes a turbine case, a turbine rotor, and an accessory generator. The turbine case extends around a central axis. The turbine rotor is mounted for rotation about the central axis and has a plurality of airfoils that extend from a base radially outward to a tip thereof. The accessory generator generates electrical power for use by the accessory system.
The accessory generator includes a stator and a plurality of magnets coupled with each of the plurality of airfoils. The stator includes 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.
In some embodiments, 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. 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.
In some embodiments, each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil. The plurality of magnets is located axially on a mid-chord of the chord of the airfoil. In some embodiments, the plurality of magnets coupled with each airfoil extends circumferentially discretely only partway around the central axis.
In some embodiments, each of the airfoils defines a chord that extends from a leading edge to a trailing edge of the airfoil. The plurality of magnets extends axially along a length of the chord between the leading edge of the trailing edge of the airfoil.
In some embodiments, 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. In some embodiments, 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.
In some embodiments, 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. 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.
These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
For the purposes of promoting an understanding of the principles of the present disclosure, reference will now be made to an illustrative embodiment shown in the drawings.
An aircraft 10 in accordance with the present disclosure can be outfitted in a modular fashion with different accessory weapons and systems as suggested in
In the illustrative embodiment, one detachable accessory unit 20 is a radar jamming pod as suggested in
The accessory system 30 included in the accessory unit 20 is illustratively made up of power electronics 35 and radar jamming electronics 36 as suggested diagrammatically in
The ram air turbine power system 32 in the illustrated embodiment integrates power generation components with turbine components to manage space claim and offer unique functionality to the accessory unit 20 as suggested in
The turbine rotor 40 includes an outer diameter 48, an inner diameter 50, airfoils 46, and bearings 52, 54, as shown in
Each airfoil 46 includes a body 56 defined by a base 60, a tip 62, a leading edge 64, and a trailing edge 66, as shown in
In some embodiments, the body 56 may also form a cavity 68, as shown in
The airfoils 46 also include a chord that is defined by a full axial length L1, as shown in
The accessory generator 42 includes a plurality of magnets 76, a stator 78, and power off-take wires 80 as shown in
The plurality of magnets 76 includes magnets arranged circumferentially adjacent to one another around the central axis 11 as shown in
As shown in
In other embodiments, the plurality of magnets 76 are formed into a magnet ring 82 coupled to the tip 62 of the airfoils 46, as shown in
In the illustrated embodiment of
The band 84 also includes a plurality of strips of metallic material 88 that extend circumferentially over the plurality of magnets 76 such that the plurality of strips of metallic material 88 axially align with the leading edge 64 and the trailing edge 66 of the airfoil 46, as shown in
In another embodiment, the magnet ring 82 is located axially on a mid-chord of the chord of the airfoil 46, as shown in
The band 84 of
In the embodiments illustrated in
For example, the plurality of magnets 76 in
The stator 78 may include concentrated or distributed windings. The stator 78 may extend circumferentially around the turbine case 38 as suggested in
In the illustrated embodiment of
The electrical generation system 93 includes the accessory generator 42 and the rectifier 35, as shown in
The cooling system 94 includes a conduit 96, cooling fluid 98 located in the conduit 96, and a controller 100, as shown in
The power off-take wires 80 extend from the stator 78 radially inward through the turbine inlet guide vanes 44, as shown in
The detachable pod or housing 34 illustratively includes attachment points 104 for coupling to hard point attachment points of the aircraft 10 as suggested in
According to the present disclosure, a ram air turbine 40 provides mechanical energy to an electrical generator 42 for DC power. In some designs, a ram air turbine 40 is a separate unit; the generator 42 is a separate unit; and the rectifier 35 is a separate unit. Designs in accordance with the present disclosure can be lighter and smaller because of the integrated solution.
In the illustrative example, the generator 42 is integrated into the airfoil tip 62 and the turbine case 38 and is arranged with the rotor magnets 76 in the airfoil tip 62 and the stator windings 78 in the turbine case 38. This eliminates a shaft and rotor of a separate generator while simplifying the overall design. The stator 78 then goes inside the turbine case 38 and exits through the inlet guide vanes 44. Designs with features like those shown can require a precise stator arrangement in order to preserve a small air gap between the stator windings 78 and magnets 76. Forward and/or aft bearings 52, 54 can provide the transition between rotating and stationary frames of reference. If required, an oil mist can cool the stator windings 78 and be scavenged out the tube containing the wires. In the illustrative example, the power electronics 35, such as the rectifier 35, controls the power offtake of the aircraft 10.
Thermal benefits may be available using designs like those discloses. Specifically, more heat can be managed with the magnets 76 coupled to the airfoil tip 62 since the airfoils 46 act as a large heat sink exposed to the incoming air stream.
There exists a need for a tightly integrated, lighter, and smaller ram air turbine 40 and generator 42 into a single unit. The ram air turbine 40 and the generator 42 may be integrated by putting the magnets 76 of the generator 42 in or at the tip 62 of the turbine blades 46 with the stator 78 radially outward of the turbine blades 46 as shown in
The turbine blades 46 may be hollow with customized tips 62 that contain the magnets 76. The magnets 76 may be in a Halbach array. A cross-section of the turbine blade 46 would show solid leading and trailing edges 64′, 66′ with corrugated stiffeners 70. The space 68 between the corrugations 70 are hollow, which would reduce the weight of the turbine blade 46. The magnets 76 are bonded to a material 59, such as bonded to metal 59, and the material 59 is bonded to the solid leading and trailing edges 64′, 66′. An airfoil skin 58 surrounds the turbine blade 46 and the magnets 76.
In other embodiments, the magnets 76 may be on top of the tips 62 of the airfoils 46 rather than embedded in the airfoil 46 and the stator 78 would be in the turbine case 38. The wiring from the stator 78 goes through the inlet guide vane 44 to reach the rectifier 35. This would eliminate the need for an output shaft to transfer torque, so the hub may be smaller than other applications. The wiring may be thick depending on the wire gauge required and the power generated.
In other embodiments, because the magnets 76 would span the entire chord-length of the airfoils 46, the height of the magnets 76 and the height of the windings 78 may be significantly reduced compared to the embodiment of
While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.
Claims
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.
Type: Application
Filed: Jul 5, 2023
Publication Date: Nov 9, 2023
Inventors: Peter M. Schenk (Greenwood, IN), Rigoberto Rodriguez (Avon, IN), David Locascio (Indianapolis, IN)
Application Number: 18/347,383