Patent Application
20250189022
The present disclosure relates to aircraft engines and, more particularly, to high-power extraction from the aircraft engine and/or supplemental power input to the aircraft engine via externally mounted accessories.
In an aircraft, gas turbine engines are used to turn propellors, fans and turboshafts during various flight operations. Gas turbine engines can also be used to drive generator operations. Additionally, supplemental power may be added to the motor or engine via an externally mounted accessory, such as an electric motor, also known as an emotor. In any case, a gearbox is typically provided and configured to take rotational energy as an input from the gas turbine engine and to transfer that rotational energy to an externally connected accessory, such as a generator.
Such a connection is typically made at an output shaft of the gas turbine engine, but it is desired to make the gas turbine engine and accessory system more compact, especially in an axial direction, and connection at this location limits the ability to do so.
In one exemplary embodiment, a reduction gearbox of an aircraft propulsion system includes an input shaft configured to input rotational energy into the reduction gearbox, an output shaft configured to output rotational energy from the reduction gearbox to a propulsor of the aircraft propulsion system, and an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft. A transfer gear is positioned at a component of the epicyclic gear arrangement and is configured to mechanically couple an accessory component to the reduction gearbox.
Additionally or alternatively, in this or other embodiments the transfer gear is positioned at a planet carrier of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the epicyclic gear arrangement is configured as one of a planetary arrangement or a solar arrangement.
Additionally or alternatively, in this or other embodiments the transfer gear is positioned at a ring gear of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the transfer gear is a bevel gear positioned at an outer circumference of one of a planet carrier or a ring gear of the epicyclic gear arrangement.
In another exemplary embodiment, a reduction gearbox and accessory component arrangement of an aircraft propulsion system includes a reduction gearbox including an input shaft configured to input rotational energy into the reduction gearbox, an output shaft configured to output rotational energy from the reduction gearbox to a propulsor of the aircraft propulsion system, and an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft. A transfer gear is positioned at a component of the epicyclic gear arrangement. An accessory component is mechanically coupled to the epicyclic gear arrangement via the transfer gear to transmit rotational energy between the reduction gearbox and the accessory component.
Additionally or alternatively, in this or other embodiments a component bevel gear is configured to mechanically couple the accessory component to the transfer gear.
Additionally or alternatively, in this or other embodiments the transfer gear is positioned at a planet carrier of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the epicyclic gear arrangement is configured as one of a planetary arrangement or a solar arrangement.
Additionally or alternatively, in this or other embodiments the transfer gear is positioned at a ring gear of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the transfer gear is a bevel gear positioned at an outer circumference of one of a planet carrier or a ring gear of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the accessory component is mechanically coupled to the transfer gear via a gear train including at least one gear train shaft.
Additionally or alternatively, in this or other embodiments the at least on gear train shaft is two gear train shafts, including a first gear train shaft coupled to the transfer gear and extending in a first direction therefrom, and a second gear train shaft coupled to the first gear train shaft and extending from the first gear train shaft in a second direction different than the first direction.
Additionally or alternatively, in this or other embodiments the accessory component is one of a generator or a motor.
In yet another exemplary embodiment, a propulsion system of an aircraft includes an engine configured to provide rotational energy to a reduction gearbox. The reduction gearbox includes an input shaft configured to input rotational energy into the reduction gearbox, an output shaft configured to output rotational energy from the reduction gearbox to a propulsor of the aircraft propulsion system, and an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft. A transfer gear is positioned at a component of the epicyclic gear arrangement, and an accessory component is mechanically coupled to the epicyclic gear arrangement via the transfer gear to transmit rotational energy between the reduction gearbox and the accessory component. A propulsor is operably connected to the output shaft and driven by rotation of the output shaft.
Additionally or alternatively, in this or other embodiments a component bevel gear is configured to mechanically couple the accessory component to the transfer gear.
Additionally or alternatively, in this or other embodiments the transfer gear is positioned at a planet carrier of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the epicyclic gear arrangement is configured as one of a planetary arrangement or a solar arrangement.
Additionally or alternatively, in this or other embodiments the transfer gear is positioned at a ring gear of the epicyclic gear arrangement.
Additionally or alternatively, in this or other embodiments the transfer gear is a bevel gear positioned at an outer circumference of one of a planet carrier or a ring gear of the epicyclic gear arrangement.
Additional features and advantages are realized through the techniques of the present disclosure. Other embodiments and aspects of the disclosure are described in detail herein and are considered a part of the claimed technical concept. For a better understanding of the disclosure with the advantages and the features, refer to the description and to the drawings.
For a more complete understanding of this disclosure, reference is now made to the following brief description, taken in connection with the accompanying drawings and detailed description, wherein like reference numerals represent like parts:
As will be described below, an aircraft engine, such as a gas turbine engine, has a reduction gearbox installed thereto including a high-power bevel gear that can be matched to a single branch triple reduction (SBTR) component for power extraction or hybrid mode. The SBTR component provides a wide range of potential speed adjustments to reach a required speed at the output from the available power gear speeds. An external accessory, such as an electrical generator or the like, is mechanically coupled to the reduction gearbox system at, for example, a planet carrier or a ring gear of the reduction gearbox system.
With reference to
Referring now to
The planet carrier 122 includes a planet bevel gear 130 located at an outer circumference of the planet carrier 122. The planet bevel gear 130 is engaged with an accessory bevel gear 132 to mechanical couple the accessory component 112 to the reduction gearbox 106. In some embodiments, the planet bevel gear 130 and accessory bevel gear 132 directly couple the reduction gearbox 106 to the accessory component 112, while in other embodiments the reduction gearbox 106 is coupled to the accessory component 112 via an accessory gear train 134, as illustrated in
With reference to
Referring now to
Another exemplary embodiment is illustrated in
Technical effects and benefits of the present disclosure are the provision of a reduction gearbox of an aircraft propulsion system in which one or more accessory components are mechanically connected to an epicyclic gear arrangement of the reduction gearbox. This configuration allows for reduction of an axial length of such arrangements compared to traditional arrangements where the accessory components are mechanically coupled to an output shaft of the reduction gearbox.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
