Aircraft tailcone incorporating an APU annular air intake

Abstract

An aircraft tailcone comprising a tailcone fuselage, a turbomachine, for example an APU, housed inside the tailcone, a ram air intake on the tailcone fuselage for the ingestion of ram air towards the interior of the turbomachine compartment, an inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented. The ram air intake extends annularly along a perimeter of the tailcone fuselage, and the inlet flap is configured such in its closed position that a surface of the inlet flap is substantially flush with the tailcone fuselage.

Claims

1. An aircraft tailcone comprising: a tailcone fuselage, a turbomachine compartment inside the tailcone fuselage, a turbomachine housed inside the turbomachine compartment, a ram air intake on the tailcone fuselage configured to cause ingestion of ram air towards the interior of the turbomachine compartment, at least one inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented, and an actuation mechanism configured to simultaneously move the at least one inlet flap from the open to the closed position, wherein the ram air intake extends annularly along at least part of a perimeter of the tailcone fuselage, wherein the inlet flap is configured such that in its open position, the inlet flap is located at least partially inside the tailcone fuselage, and in its closed position a surface of the inlet flap is substantially flush with a tailcone fuselage surface, and wherein the actuation mechanism comprises an L-shaped lever having first and second angled arms with respect to a first pivot point, wherein the second arm has a groove, such that a straight arm has a first end mounted at the groove, and a second end is coupled with an actuation point of the inlet flap.

2. The aircraft tailcone according to claim 1, wherein the annular ram air intake extends annularly along an entire perimeter of the tailcone fuselage.

3. The aircraft tailcone according to claim 1, further comprising a plurality of inlet flaps adjacent to each other and covering the annular ram air intake in their closed position.

4. The aircraft tailcone according to claim 1, wherein each inlet flap is a curved body having a leading edge and a trailing edge which is thinner than the leading edge, and a pivot point near the leading edge so that the inlet flap pivots about the pivot point to move reciprocately from the open position to the closed position.

5. The aircraft tailcone according to claim 1, wherein the actuation mechanism further comprises a plurality of the L-shaped levers and an actuation ring placed vertically at the tailcone, and adapted to move horizontally, and wherein the actuation ring is inserted through a point on the first arm of all the levers to move all the levers simultaneously.

6. The aircraft tailcone according to claim 5, wherein the actuation mechanism is configured so that by moving the actuation ring forward towards a nose of the aircraft, all the levers move clockwise as viewed from a port side of the aircraft and the arms pull the inlet flap downwards to the open position, and by moving the actuation ring backwards towards a rear of the aircraft, all the levers move counter-clockwise as viewed from a port side of the aircraft and the arms push all the inlet flaps upwards to the closed position.

7. The aircraft tailcone according to claim 1, wherein the turbomachine is an Auxiliary Power Unit.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Preferred embodiments of the invention, are henceforth described with reference to the accompanying drawings, wherein:

(2) FIG. 1 shows a side elevational view of a commercial aircraft of the prior art, wherein the location of the tailcone is identified.

(3) FIG. 2 shows a schematic representation in a side elevational view of an APU compartment according to the prior art.

(4) FIG. 3 shows a schematic representation in a side elevational view of an aircraft tailcone according to the invention. The arrows illustrate the ram air ingestion towards the turbomachine compartment.

(5) FIG. 4 shows a schematic representation of an inlet flap according to the invention.

(6) FIG. 5 shows a schematic representation in a perspective view, of an annular air intake duct according to the invention. The open and closed position of an inlet flap is represented in the figure, wherein the closed position is shown in broken lines and the open position of the inlet flap is represented in continuous line.

(7) FIG. 6 shows an elevational view of the inlet flap actuator according to a preferred embodiment of the invention.

(8) FIG. 7 shows a schematic representation of a flap actuator ring according to a preferred embodiment of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

(9) FIG. 3 shows an aircraft tailcone (1) comprising a tailcone fuselage (2), and a turbomachine compartment (3) inside the tailcone fuselage (1). A turbomachine (4) is housed inside the turbomachine compartment (3) such as the combustion gases are discharged to the outside through an exhaust (5).

(10) The tailcone (1) incorporates an annular air intake (6) that in this preferred embodiment extends annularly along an entire perimeter of the tailcone fuselage (2) as shown in FIGS. 3 and 5. The perimeter is to be understood as to be laying on a plane transversal to the longitudinal axis (X) of the tailcone (1).

(11) Furthermore, the aircraft tailcone (1) comprises a plurality of inlet flaps (7) adjacent to each other and operable reciprocately between an open position in which ingestion of ram air is allowed towards the interior of the turbomachine compartment (see arrows in FIG. 3), and a closed position (represented with dotted lines in FIG. 3) in which ram air ingestion is prevented. Preferably, the entire annular air intake (6) is covered by inlet flaps (7) that move simultaneously in such a way that in the open position ram air is ingested from all around the annular air intake (6).

(12) As represented at the upper part of FIG. 3, the inlet flaps (7) are configured such in their open position that they are received inside the tailcone fuselage (2). In their closed position, an outer surface of the inlet flaps (7) is substantially flush with the tailcone fuselage (2) (see FIG. 5), such that the surface of tail cone fuselage (2) is continuous on the air intake area, and no drag is generated in that no element protrudes outside the fuselage.

(13) As shown in FIG. 4, each inlet flap (7) is a curved body that has a leading edge (9) and a trailing edge (10) which is thinner than the leading edge (9). The curvature of each inlet flap (7) matches the curvature and shape of a particular section of the annular air intake (6). There is a pivot point (8) near the leading edge (9), and an actuation point (11) near the trailing edge (10). Each inlet flap (7) is fixed to the tailcone at the pivot point (8), and by actuating at the actuation point (11), the inlet flap (7) pivots about the pivot point (8) to move reciprocately from the open position to the closed position as represented in FIG. 5.

(14) There are many possible ways to operate the inlet flaps (7). FIGS. 6 and 7 show an exemplary embodiment of an actuation mechanism, comprising a L-shaped lever (12) having first and second angled arms (12a,12b) with respect to a pivot point (13). The first arm (12a) has a point (14) which pivots relative to an actuation ring (18) (described below), and the second arm (12b) has a groove (15), such that a straight arm (16) has a first end (17) articulated at the groove (15) and a second end articulated with the actuation point (11) of the inlet flap (7).

(15) Even though only one inlet flap (7) and only one actuation mechanism is represented in FIGS. 5 to 7 for the sake of the clarity of the figures, it is to be understood that in a practical embodiment, a plurality of inlet flaps (7) coupled with the respective actuation mechanisms, are installed all around the annular air intake (6).

(16) The actuation ring (18) is placed vertically at the tailcone and adapted to move horizontally as illustrated in FIG. 7. The actuation ring (18) is inserted in the pivot point (14) of all the levers (12) so that by moving the actuation ring (18) forward (to the left in FIG. 7), all the levers (12) would move clockwise, thus causing the levers (12) to pivot relative to the actuation ring (18) at the pivot point (14) and the arms (16) would pull the inlet flaps (7) downwards to the open position. For moving the inlet flaps (7) to the closed position, the actuation ring (18) is moved backwards (to the right in FIG. 7) so that all the levers (12) would move counter-clockwise, and the arms (16) would push all the inlet flaps (7) upwards to the closed position.

(17) An actuator (19), for example a hydraulic or pneumatic cylinder, coupled with the actuation ring (18) is responsible for moving the actuation ring (18).

(18) The above-described mechanism for operating (opening and closing) the annular air intakes, provides redundancy so that the system will be able to operate even if one or more of the individual actuators fails, thereby, enhancing the system reliability.

(19) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.