Embraer S.a.

Usp—universidade De São Paulo

Universidade De São Paulo-Usp

Micael Gianini Valle Do Carmo

Leandro Guilherme Crenite Simões

Francisco Keller Klug

Danillo Cafaldo Dos Reis

Cecil Wagner Skaleski

Marcus Felipe Hori Ochi

Fernando Martini Catalano

Leandro Souza De Moura Lima

Eduardo Lobão Capucho Coelho

Vinicius Losada Gouveia

Paulo Anchieta Da Silva

Fábio Santos Da Silva

Bruno Arantes Caldeira Da Silva

Mário Trichês, Jr

Mário Triches, Jr

Alexandre Viana Ferreira

Alysson Kennerly Colaciti

Gilson Atanásio

Reginaldo Faisca Fermiano

Marcus Vinicius Franca Barboza

Marcus Vinícius Franca Barboza

Mário Júnior TRICHÊS

Vinícius Losada Gouveia

Leandro Guilherme Crenite Simoes

Joabe Marcos De Souza

Lourenço Tércio Lima Pereira

Leandro Guilherme Crenite SIMÕES

Danilo Cafaldo Dos Reis

Exhaust nozzles for outflow valves (OFVs) that are usefully employed in aircraft pressurization systems include an upstream solid (e.g., cylindrical) wall section and a downstream solid exhaust wall section fixed to the upstream solid wall section. The downstream solid exhaust wall section includes a circumferential portion defining a series of air intake perforations. A pair of vortex generators may also be provided upstream of the series of air intake perforations. The air intake perforations and optional vortex generators thereby allow air from the ambient pressure environment to be introduced into the boundary layer of pressurized air discharged by the OFV in the interior of the perforated region of the downstream solid exhaust wall section of the nozzle thereby reducing adverse pressure gradients therewithin which in turn results in a more attached air flow and hence less perceived noise.

Low noise outflow valve exhaust nozzle for aircraft pressurization systems

Noise-abatement for a leading edge wing slat is provided by a noise-abatement airflow shield integral with the lower trailing edge of the slat, wherein the shield is reciprocally autonomously curveable from a substantially planar configuration when the slat is in a retracted position thereof and into a convexly curved configuration when the slat is in a deployed position thereof.

Retractable leading edge wing slats having autonomously curvable airflow shield for noise-abatement

Noise-abatement systems provide noise abatement to a wing assembly provided with a forward edge slat and include an elongate shield element which is unconnected but positionable adjacent to a lower trailing edge of the edge slat along a lengthwise extent thereof, and a support web having a distal end fixed to the shield element and a proximal end capable of fixation to an interior cove surface of the edge slat adjacent an upper trailing edge thereof. The support web will therefore allow movement of the shield element towards and away from the lower trailing edge of the edge slat between an operative position wherein the shield element is positioned adjacent to the lower trailing edge of the edge slat along the lengthwise extent thereof and an inoperative position wherein the edge slat is spaced from the trailing edge of the edge slat and positioned in the cove region thereof, respectively.

Noise abatement systems for retractable leading edge wing slats of an aircraft wing assembly

Flap track fairing systems are split into a forward immovably fixed portion and an aft movable portion. The fixed forward portion is immovably attached to the main wing structure of an aircraft while the movable aft portion is attached either to the movable components of the flap deployment mechanism or to the lower surface of the flap. A separation line between the forward movable portion and the aft fixed portion is provided such that the movable portion does not interfere structurally with the flap fairing structure during a flap extension/retraction cycle. An airflow deflector is positioned near a forward separation edge of the aft fairing portion so as to be positioned within a gap defined between the forward edge of the aft fairing portion and a rearward edge of the forward fairing portion when the flap is in the deployed configuration thereof to thereby deflect airflow away from the interior space of the fairing.

Airfoil flap assembly with split flap track fairing system

Aircraft are provided with a perforated blade seal at the lower and/or upper side edges of a control surface contour, such as a flap, with the purpose of acting as a vortex generator, thereby making it difficult for the lower vortex system to move upwards and merge with the upper vortex system. The perforated blade seals are preferably arranged on the inboard and outboard edges of high lift flaps.

Aircraft provided with aerodynamic seal for reduction of noise generated by aircraft control surfaces

Growing community of inventors

São José dos Campos, Brazil

Micael Gianini Valle Do Carmo