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KR-102963409-B1 - AIRCRAFT PROVIDED WITH A RAIN-REPELLENT VENTILATION SYSTEM FOR AN ELECTRIC MACHINE

KR102963409B1KR 102963409 B1KR102963409 B1KR 102963409B1KR-102963409-B1

Abstract

The present invention relates to an aircraft (1) having at least one electric machine (17) housed in a compartment (5) separated from the external environment (EXT) by a cowling (10), wherein the aircraft (1) includes a ventilation system (30) for delivering air from the external environment (EXT) to the electric machine (17). The ventilation system (30) includes a duct (35) connected to an electric machine (17) and extending to a free section (37), the free section (37) being located in the external environment (EXT), the duct (35) passing through a passage (11) inside the cowling (10), the duct (35) extending partly into the compartment (5) and partly into the external environment (EXT), the free space (12) surrounding the duct (35) in the passage (11) and separating the duct (35) from the cowling (10), and the ventilation system (30) includes a scoop (50) that is not closed and faces the free section (37) along the vertical axis (DIRV) when the aircraft (1) is on the horizontal ground (100).

Inventors

  • 파트릭 포르
  • 파스칼 알리오

Assignees

  • 에어버스 헬리콥터스

Dates

Publication Date
20260512
Application Date
20240226
Priority Date
20230609

Claims (14)

  1. An aircraft (1) provided with at least one electric machine (17) housed in a compartment (5) of the aircraft (1), The above compartment (5) is separated from the external environment (EXT) by a cowling (10), and The above external environment (EXT) is located outside the aircraft (1), and The aircraft (1) includes a ventilation system (30) for delivering air from the external environment (EXT) to the electric machine (17), and The ventilation system (30) includes a duct (35) that is connected to the electric machine (17) and extends to a free section (37), and The above free section (37) is located in the above external environment (EXT), and The above duct (35) passes through the passage (11) inside the cowling (10), and The above duct (35) extends partially into the interior of the compartment (5) and partially into the external environment (EXT), and The free space (12) surrounds the duct (35) in the passage (11) and separates the duct (35) from the cowling (10), and The above ventilation system (30) is an aircraft (1) that includes a scoop (50) facing a free section (37) without being closed.
  2. In paragraph 1, The aircraft (1) is characterized in that the scoop (50) and the cowling (10) form a corridor (60) that extends along an extension axis (DIREXT) from a first surface (61) open to the external environment (EXT) to a second surface (62) open to the external environment (EXT).
  3. In paragraph 2, The aircraft (1) is characterized in that the above extension axis (DIREXT) is parallel to the roll axis (AXROL) of the aircraft (1).
  4. In paragraph 1, The above duct (35) is characterized by including at least one drain (70) upstream of the electric machine (17) in a direction toward the electric machine (17) from the external environment (EXT), in the aircraft (1).
  5. In paragraph 4, The above duct (35) includes an intake segment (39) passing through the cowling (10) and an outlet segment (38) connected to the intake segment (39) leading to the electric machine (17). The above exit segment (38) extends along the extension axis (AX1) of the extension of the electric machine (17), and The intake segment (39) extends along the elevation axis (AX2) from the outlet segment (38) to the external environment (EXT), and The aircraft (1) is characterized in that the above drain (70) is formed in the outlet segment (38).
  6. In paragraph 1, The aircraft (1) is characterized in that the above duct (35) is connected by at least one fastener (76) to a structure (75) that is fixed to the reference frame (X, Y, Z) of the aircraft (1).
  7. In paragraph 6, The aircraft (1) is characterized in that the above duct (35) includes freedom of movement limited to a range of positions related to the structure (75).
  8. In paragraph 1, The above passage (11) is characterized by being rectangular, an aircraft (1).
  9. In paragraph 1, An aircraft (1) characterized in that the minimum distance (200) separates the edge (13) of the cowling that defines the boundary of the passage (11) from the duct, and the minimum distance (200) is 5 mm to 20 mm.
  10. In paragraph 1, The aircraft (1) is characterized in that the above duct (35) protrudes from the cowling into the external environment (EXT) by a minimum height of 5 mm to 20 mm.
  11. In paragraph 1, The above scoop (50) is positioned between the passage (11) and the rotor (25) of the aircraft (1), and the rotor (25) is located in the external environment (EXT), characterized by the aircraft (1).
  12. In paragraph 1, The above ventilation system (30) is characterized by including at least one protective screen (81, 82), an aircraft (1).
  13. In Paragraph 12, The above protective screen (81) is characterized by being placed in the above free section (37), an aircraft (1).
  14. In Paragraph 12, The above protective screen (82) is characterized by being positioned between the scoop (50) and the cowling (10), in an aircraft (1).

Description

Aircraft provided with a rain-repellent ventilation system for an electric machine This application claims priority to FR 23 05863 filed on June 9, 2023, the entire disclosure of which is incorporated herein by reference. The present invention relates to an aircraft equipped with a rainwater prevention ventilation system for electric machinery. An aircraft typically includes a power unit comprising at least one engine and at least one gearbox. For example, a rotary-wing aircraft is provided with at least one engine to rotate at least one rotor through a gearbox. This rotor contributes at least partially to the lift and/or thrust of the rotary-wing aircraft. Engines or engines may be housed in an engine compartment separated from the aircraft exterior by cowling. The term "coowling" may refer to a cowl, a movable structure, a fairing, a profile, or a partitioned box. Engines or engines can be heat engines supplied with fuel and air. Furthermore, the aircraft may include electrical machinery. The electrical machinery may take the form of electrical power generation means capable of converting mechanical energy into electrical energy, electric motors capable of converting electrical energy into mechanical energy to operate mechanical systems, or starter-generators connected to a thermal engine to start the thermal engine or to produce electrical energy as needed. For example, a starter-generator may be kinematically connected to the gas generator of a turboshaft engine. These electrical machines can generate heat during operation. Therefore, aircraft may include a ventilation system to cool the electrical machines by drawing in cold air from the outside. While effective, the aircraft may encounter rain, and unwanted rainwater could come into contact with the electrical machines. Literature describing engine air intakes is far removed from this problem. For example, patent document US 2020 0 023 985 A1 describes a system having an air intake that accommodates a filter and is covered by a scoop. Patent document US 2 362 552 A also describes a scoop placed over an air intake opening. Patent document FR 3 065 757 D1 describes an air intake that works in cooperation with a diffuser. Patent document US 2019/093541 relates to an aircraft equipped with an exhaust collector that provides one or more conduits for delivering and discharging exhaust gases upward. The exhaust collector includes a support structure for a cowl located on the top and/or side of the aircraft. Patent document US 2 362 552 describes an air intake scoop designed to separate air from other incoming particles and heavy substances such as water droplets and ice, for example, to supply fresh air to an aircraft cabin or engine. Patent document CA 3 055 979 describes a ventilation system for a helicopter engine compartment comprising an ejector nozzle, four air intakes, two air plenums, and two air slots. The ejector nozzle surrounds the exhaust pipe inlet of the engine and uses the flow of exhaust gas to direct air toward the inside of the engine compartment, through the engine compartment, and to the outside of the engine compartment. Two air intakes are connected to the front of the engine compartment of the helicopter fuselage and supply air to two air plenums. Two additional air intakes are connected to the front of the engine compartment and supply air to the upper area of the engine compartment. Patent documents EP 3 560 837 A1, US 2019 0 084 687 A1, EP 3 418 183 A1, EP 3 403 919 A1, FR 3 026 136 A1, FR 3 021 994 A1, EP 2 880 295 A4, EP 2 776 319 A1, EP 2 226 473 A3, EP 1 828 571 A1, US 3 208 214 A, US 2 362 552 A and US 2 365 328 A are also known. The present invention and its advantages are further explained in the following description of the given embodiments through examples and with reference to the accompanying drawings. FIG. 1 is a three-dimensional diagram illustrating a part of an aircraft according to the present invention. Figure 2 is a partial transparency of the aircraft in Figure 1. Figure 3 is a diagram showing a plan view of a duct passing through the passage of a cowling. Figure 4 is a diagram illustrating the scoop. Elements present in two or more drawings are provided with the same reference number in each drawing. FIGS. 1 to 4 illustrate a reference frame of an aircraft (1) according to the present invention. This reference frame is composed of three mutually orthogonal axes, X, Y, and Z. The X-axis is called the longitudinal axis. The term "longitudinal" refers to the direction parallel to this X-axis. The Y-axis is called the transverse axis. The term "transverse" refers to the direction parallel to this Y-axis. Finally, the Z-axis is called the altitude axis. The term "altitude" refers to any direction parallel to this Z-axis. FIG. 1 schematically illustrates an aircraft (1) according to the present invention. The aircraft (1) is partially illustrated so as not to unnecessarily complicate FIG. 1. The aircraft is provided