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Annular acoustic panel

A sound insulation board and annular technology, applied in the field of integral annular sound insulation boards, can solve the problems of noise escaping, sound insulation area loss of function, difficult acoustic processing, matching of acoustic absorption characteristics, etc.

Active Publication Date: 2006-11-15
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Acoustic areas are also lost between the individual baffles, between the baffle and the nacelle inlet structure, and between the baffle and the nacelle engine structure adjacent to the surface of the fan blades in the fan assembly
Additionally, the number of baffles that a typical acoustic treatment system contains can make it difficult to "tune" the acoustic treatment to best match the source noise
Namely, it is difficult to match the acoustic absorption characteristics of acoustic treatments to the noise characteristics of a particular engine and associated fan assembly
In addition, typical acoustic treatment systems have multiple leak paths that allow air to escape from the engine assembly so that the noise can also escape
In addition, in existing acoustic treatment systems, a higher part count would increase aircraft weight and increase manpower and part costs

Method used

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Examples

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Embodiment Construction

[0010] figure 1 is a partial longitudinal sectional view of an aircraft engine assembly 10 according to the invention. The engine assembly includes an engine 14 , such as a gas turbine, and an associated fan assembly 18 . The fan assembly 18 includes a plurality of circumferentially spaced fan blades 22 . Surrounding the engine 14 and fan blades 22 is a nacelle 26 spaced radially outward from the engine 14 to define an annular passage 30 . Thrust generating air used by the engine assembly 10 enters the engine assembly in the X direction. Typically, air enters nacelle 26 , is compressed by fan blades 22 , and flows through engine 14 via passages 30 .

[0011] Nacelle 26 includes an inlet portion 34 connected to a main portion 38 that supports engine 14 and fan assembly 18 within nacelle 26 . The connection between the inlet section 34 and the main section 38 includes a main bulkhead 42 which is used at the connection to provide structural integrity and strength to the nacel...

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Abstract

An aircraft engine assembly (10) is provided that is adapted to reduce noise produced by an engine (14) included in the engine assembly. The engine assembly (10) includes a nacelle (26) having an inlet section (34) and a main section (38) that is houses the engine (14) and fan assembly (18) associated with the engine. The inlet section (34) is coupled to the main section (38) at a main bulkhead (42) junction between the inlet section (34) and the main section (38) . A one piece annular acoustic panel (46) is located within a recess in an internal wall (54) of the nacelle (26) . The annular acoustic panel (46) extends from a forward portion of the inlet section (34) to a forward portion of the main section (38) such that the bulkhead (42) is covered by the annular acoustic panel (46).

Description

technical field [0001] The present invention generally relates to inlet absorption and attenuation of aircraft engine noise. More specifically, the present invention relates to an integral annular sound baffle panel extending inwardly from the front of the engine nacelle inlet, across the junction of the nacelle inlet and the nacelle engine structure, and into the engine structure. Background technique [0002] Airline aircraft are required by law to meet specified engine noise standards. Typically, existing aircraft engine acoustic treatment systems include a series of individual panels mounted in sections within the engine fan case. Typically, the baffle is located immediately aft of the engine / inlet attachment interface and in front of the engine fan assembly. At least one existing engine acoustic treatment system includes a plurality of individual panels mounted side-by-side around the interior surface of the engine fan case and / or within the interior of other adjacent...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02B64D29/00F02C7/045F02K1/82
CPCB64D29/00B64D33/02B64D2033/0206F02C7/045F02K1/827F05D2260/96Y02T50/60
Inventor 杰弗里·E·哈里森
Owner THE BOEING CO
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