Patent ID: 12215591

DESCRIPTION

In the following description, reference is made to the accompanying drawings which form a part hereof, and which is shown, by way of illustration, several embodiments. It is understood that other embodiments may be utilized and structural changes may be made without departing from the scope of the present disclosure.

Technical Description

FIG.1illustrates the pylon71rotates the entire engine pod60by the engine toe angle75so as to increase alignment of the inlet with the sidewash and increase flow of air into the intake duct78. However, rotation of the entire engine pod60points the thrust vector73of the thrust in a non-optimal direction (i.e., the thrust vector73is no longer parallel to the direction of desired propagation).

The present disclosure describes a horizontally drooped inlet that aligns just the inlet and/or a forward portion of the nacelle while keeping the back of the nozzle pointing in a more optimal direction (e.g., parallel to the engine centerline) so as to increase overall performance of the engine and reduce fuel consumption. An example inlet is described in the following sections.

Example Inlet

FIGS.2A-2Billustrate an aircraft part200comprising an inlet202for a nacelle. The inlet202comprises an inlet leading edge204(also known as a highlight206), the highlight206has an outboard side208and an inboard side210, and the outboard side208is forward of the inboard side210.

FIG.2Cillustrates the highlight206lies in a first plane212inclined at an angle214with respect to the engine centerline216. Example angles214include, but are not limited to, an angle214in a range of half a degree to 3 degrees, an angle214equal to an engine toe angle75, or an angle214tuned to increase an input of the airflow218(comprising a sidewash deflection) into the inlet202.

FIG.2Cfurther illustrates the dimensions of the inlet202relative to the fan64inputting a portion of airflow218into the gas turbine engine (e.g.,61inFIG.1). The fan64having a diameter D comprises a hub63(comprising a hub leading edge224) and the inlet202comprises an inboard length226and an outboard length230. The inboard length comprises a first perpendicular distance from a second plane228, comprising the hub leading edge224, to the inlet leading edge204on the inboard side210. The outboard length230comprises a second perpendicular distance from the second plane228to the inlet leading edge204on the outboard side208, such that the outboard length230is longer than the inboard length226.

Example Nacelle

FIG.3AandFIG.3Billustrates an example nacelle300including the inlet202. The nacelle300houses a gas turbine engine (e.g.,61inFIG.1) having the engine centerline216(which is the same as the engine centerline80comprising central longitudinal axis of drive shaft) and generating a thrust302having a thrust vector304. As illustrated inFIG.3A(referring also toFIGS.2B-2C) the outboard side208of the inlet202is forward of the inboard side210of the inlet202, so that the inlet202has an inlet centerline306aligned inboard or inwards toward the fuselage, so as to increase an airflow218into the inlet202and allow increased alignment of the thrust vector with the engine centerline when the airflow218comprises sidewash.

FIGS.3A and3Bfurther illustrate the outboard side208comprises a point on the highlight206furthest from the fuselage (402inFIG.4A) or closest to the tip of the wing (wingtip450inFIG.4) when the nacelle300is mounted on the wing; and the inboard side210comprises a point on the highlight206closest to the fuselage402and furthest from the wingtip450.

In one or more examples, the nacelle is symmetrical about the engine centerline aft of a predetermined position308and/or a curvature310of the nacelle is blended to increase aerodynamics in flow around the nacelle.

Example Aircraft

FIG.4Aillustrates an aircraft400comprising a fuselage402having a longitudinal axis404, wings406attached to the fuselage402, and aircraft engines408comprising engine pods410mounted to the wings, wherein each engine pod410is mounted to the wing via a mount412(e.g., a pylons414). The engine pods410each comprise an inlet202and nacelle300housing a gas turbine engine (e.g.,61inFIG.1) according to embodiments described herein. In one or more examples, the mounts412mount the engine pods410so that the thrust vector304, generated by the exhaust outputted from the gas turbine engine, is parallel to the engine centerline216and the engine centerline216is parallel to the longitudinal axis404of the fuselage402(i.e., the engine toe angle75is zero). In one or more examples, reducing the engine toe angle75from 1 degree to 0 degrees toe while using an inlet202as described herein reduces fuel consumption by ˜0.2%. In other examples, the engine pod410comprising inlet202is mounted with a reduced engine toe angle75as compared to the engine with the conventional inlet72illustrated inFIG.1.

FIG.4Afurther illustrates a sidewash deflection312comprising airflow218deflected by the fuselage402. As illustrated inFIG.2B, the angle214of inclination of the highlight206with respect to the engine centerline80is tuned to compensate for the sidewash deflection312and match the airflow218into the gas turbine engine61for increased thrust in a presence of the sidewash deflection.

FIG.4Billustrates an example wherein the aircraft400comprises a flying wing450and the wing406includes the fuselage402. Aircraft engines408comprising the inlet202are mounted to the flying wing.

Example Process Steps

FIG.5is a flowchart illustrating a method of making an inlet, a nacelle, an aircraft engine, and an aircraft.

Block500fabricating the inlet for a nacelle housing a gas turbine engine, the gas turbine engine having an engine centerline and generating a thrust having a thrust vector. The inlet is fabricated so that the inlet comprises a highlight comprising an inlet leading edge, the highlight has an outboard side and an inboard side, and the outboard side is forward of the inboard side of the highlight so as to increase the airflow into the inlet and allow increased alignment of the thrust vector with the engine centerline. In some examples, the inlet has an inboard length comprising a first perpendicular distance from a plane, comprising the hub leading edge, to the inlet leading edge on the inboard side, an outboard length comprising a second perpendicular distance from the plane to the inlet leading edge on the outboard side, and the outboard length is longer than the inboard length.

Block502represents attaching the inlet to a nacelle or fabricating the nacelle having the inlet.

Block504represents housing a gas turbine engine (having an engine centerline) and a fan in the nacelle so that the fan inputs a portion of the airflow into the gas turbine engine.

Block506represents mounting the aircraft engine to an aircraft, comprising a wing and a fuselage, using a mount. In various examples, the mount mounts the aircraft engine so that the thrust vector is parallel to the engine centerline.

Illustrative, non-exclusive examples of inventive subject matter according to the present disclosure are described in the following enumerated paragraphs:

A1. An aircraft part (200), comprising:an inlet (202) for a nacelle (300) housing a gas turbine engine (61), the gas turbine engine (61) having an engine centerline (216) and generating a thrust (302) having a thrust vector (304), the inlet (202) further comprising:a highlight (206) comprising an inlet leading edge (204) of the inlet (202), wherein:the highlight (206) has an outboard side (208) and an inboard side (210); andthe outboard side (208) is forward of the inboard side (210) so as to increase an airflow (218) into the inlet (202) and allow an increased alignment of the thrust vector (304) with the engine centerline (216).

A2. The aircraft part (200) of paragraph A1, wherein the highlight (206) lies in a plane (212) inclined at an angle (214) with respect to the engine centerline (216).

A3. The aircraft part (200) of paragraph A2, wherein the angle (214) is in a range of half a degree to 3 degrees (e.g., 0.5°≤angle≤3°).

A4. The aircraft part (200) of paragraph A1 or A2, wherein the angle (214) is equal to an engine toe angle (75).

A5. The aircraft part (200) of paragraph A4, wherein the airflow (218) comprises a sidewash deflection (312) and the angle (214) is tuned to increase an input of the sidewash deflection (312) into the inlet (202).

A6. An aircraft engine (408) comprising the aircraft part (200) of any of the paragraphs A1-A5, further comprising:the nacelle (300) housing the gas turbine engine (61) and a fan (64) inputting a portion of the airflow (218) into the gas turbine engine (61), the fan (64) comprising a hub (63) connected to fan (64) blades and the hub (63) comprising a hub leading edge (224); andthe inlet (202) comprising:an inboard length (226) comprising a first perpendicular distance from a plane (228), comprising the hub leading edge (224), to the inlet leading edge (204) on the inboard side (210),an outboard length (230) comprising a second perpendicular distance from the plane (228) to the inlet leading edge (204) on the outboard side (208), and wherein:the outboard length (230) is longer than the inboard length (226).

A7. An aircraft (400) comprising the aircraft engine (408) of paragraph A6.

A8. The aircraft (400) of paragraph A7, wherein the aircraft (400) comprises a wing (406) and a fuselage (402), the aircraft (400) further including a mount (412) mounting the aircraft engine (408) to at least one of the wing (406) or the fuselage (402), wherein the mount (412) mounts the aircraft engine (408) so that the engine centerline (216) has an engine toe angle (75) of 1 degree or less with respect to a longitudinal axis (404) of the fuselage (402).

A9. The aircraft engine (408) of paragraph A8, wherein the engine centerline (216) is parallel to the longitudinal axis (404) of the fuselage (402).

A10. The aircraft engine (408) of paragraph A8 or A9, wherein the airflow (218) comprises a sidewash deflection (312) deflected by the fuselage (402) and an angle (214) of inclination of the highlight (206) with respect to the engine centerline (216) is tuned to compensate for the sidewash deflection (312) and match the airflow (218) into the gas turbine engine (61) for increased thrust (302) in a presence of the sidewash deflection (312).

A11. The aircraft engine (408) of any of the paragraphs A1-A10, wherein the nacelle (300) is symmetrical about the engine centerline (216) aft of a predetermined position (308).

A12. The aircraft engine (408) of any of the paragraphs A1-A11, wherein a curvature (310) of the nacelle (300) is blended to increase aerodynamics of a portion of the airflow (218) around the nacelle (300).

A13. The aircraft engine (408) of any of the paragraphs A8-A12, wherein the aircraft (400) comprises a flying wing (450) and the wing (406) includes the fuselage (402).

A14. The aircraft engine (408) of any of the paragraphs A8-A13, wherein the aircraft engine (408) is mounted to the wing (406) or an empennage of the aircraft (400).

A15. A method of making an aircraft part (200), comprising: fabricating an inlet (202) for a nacelle (300) housing a gas turbine engine (61), the gas turbine engine (61) having an engine centerline (216) and generating a thrust (302) having a thrust vector (304); wherein the inlet (202) comprises:a highlight (206) comprising an inlet leading edge (204) of the inlet (202), wherein:the highlight (206) has an outboard side (208) and an inboard side (210); andthe outboard side (208) is forward of the inboard side (210) so as to increase an airflow (218) into the inlet (202) and allow an increased alignment of the thrust vector (304) with the engine centerline (216).

A16. The method of paragraph A15, further comprising:attaching the inlet (202) to the nacelle (300) or fabricating the nacelle (300) having the inlet (202);housing the gas turbine engine (61) and a fan (64) in the nacelle (300) so that the fan (64) inputs a portion of the airflow (218) into the gas turbine engine (61), the fan (64) comprising a hub (63) connected to fan (64) blades and the hub (63) comprising a hub leading edge (224); and wherein fabricating the inlet (202) further comprises fabricating the inlet (202) having:an inboard length (226) comprising a first perpendicular distance from a plane (228), comprising the hub leading edge (224), to the inlet leading edge (204) on the inboard side (210),an outboard length (230) comprising a second perpendicular distance from the plane (228) to the inlet leading edge on the outboard side (208), and wherein the outboard length (230) is longer than the inboard length (226).

A17. The method of paragraph A15 or A16, further comprising mounting the nacelle (300) to an aircraft (400) comprising a wing (406) and a fuselage (402) using a mount (412), wherein the mount (412) mounts (412) the nacelle (300) so that the engine centerline (216) has an engine toe angle (75) angle (214) of 1 degree or less with respect to a longitudinal axis (404) of the fuselage (402).

A18. The method of any of the paragraphs A15-A17, wherein the highlight (206) lies in a plane (212) inclined at an angle (214) with respect to the engine centerline (216).

A19. The method of paragraph A18, wherein the angle (214) is in a range of half a degree to 3 degrees (e.g., 0.5°≤angle≤3°).

A20. The method of paragraph A18 or A19, wherein the angle (214) is equal to an engine toe angle (75), the airflow (218) comprises a sidewash deflection (312), and the angle (214) is tuned to increase an input of the sidewash deflection (312) into the inlet (202).

A21. A jet engine, comprising a nacelle inlet with a horizontal droop (NIHD), where the inlet is drooped to the fuselage side of the aircraft, and where the engine inlet and forward portion of the nacelle are aligned horizontally enabling an optimum pointing of the nozzle of the jet engine.

A22. The inlet (202) of any of the examples, comprising a solid of revolution about an axis of revolution comprising the engine centerline (216).

Those skilled in the art will recognize many modifications may be made to this configuration without departing from the scope of the present disclosure. For example, those skilled in the art will recognize that any combination of the above components, or any number of different components, peripherals, and other devices, may be used.

CONCLUSION

This concludes the description of the preferred embodiments of the present disclosure. The foregoing description of the preferred embodiment has been presented for the purposes of illustration and description. It is not intended to be exhaustive or to limit the disclosure to the precise form disclosed. Many modifications and variations are possible in light of the above teaching. It is intended that the scope of rights be limited not by this detailed description, but rather by the claims appended hereto.