公开(公告)号：US20190300188A1

公开(公告)日：2019-10-03

申请号：US15943963

申请日：2018-04-03

申请人： Rohr, Inc.

发明人： Mark R. Gurvich ,  Georgios S. Zafiris ,  Jeffrey A. Anderson ,  Jose S. Alonso-Miralles ,  Milan Mitrovic ,  Terry Muy ,  George Hoehn ,  Timothy Olson

IPC分类号： B64D29/00 ,  G10K11/168

摘要： A panel is provided for attenuating sound. This panel includes a perforated first skin, a second skin and a core. The core forms a plurality of cavities vertically between the perforated first skin and the second skin. The core includes an array of corrugations that include a first baffle, a second baffle and a first septum. The cavities include a first cavity formed longitudinally between the first baffle and the second baffle. The first cavity is fluidly coupled with perforations in the first skin. The first septum extends from the first skin and the first baffle to the second skin and the second baffle. The first septum divides the first cavity into fluidly coupled sub-cavities. At least one element of the panel includes at least one first rib and at least one second rib, the first rib extends along a first trajectory and the second rib extends along a second trajectory that is non-parallel with the first trajectory.

公开(公告)号：US20190161200A1

公开(公告)日：2019-05-30

申请号：US16260972

申请日：2019-01-29

申请人： Safran Nacelles ,  Safran Aircraft Engines

发明人： Marc VERSAEVEL ,  Denis RAMAGE ,  Baptiste CORDIER ,  Georges RIOU ,  Jacky MARDJONO

IPC分类号： B64D33/02 ,  F02C7/045 ,  F02C7/24 ,  F02K1/82 ,  B64D29/00

摘要： An acoustic attenuation panel for a propulsion unit including a nacelle and a turbojet engine includes a cellular core disposed between an inner skin and an outer skin, called acoustic skin, the acoustic skin including a plurality of acoustic apertures, the acoustic apertures being inclined, at a non-zero inclination angle (β) relative to the direction normal to the acoustic skin, upstream with respect to the flow direction of the air or gas flow to which the panel is intended to be subjected under normal operating conditions, that is to say upstream of the propulsion unit when the panel is mounted in such a unit.

公开(公告)号：US10301973B2

公开(公告)日：2019-05-28

申请号：US15100225

申请日：2014-12-02

申请人： Snecma

发明人： Alexandre Leon ,  Gilles Brun

IPC分类号： F01D25/32 ,  F01D25/24 ,  F02K3/06 ,  B64C1/14 ,  B64D29/00

摘要： A device for retaining drained fluids for a propulsive assembly includes a cavity for storing the drained fluids and two walls mounted at the opening of said cavity. The cavity has a fluid storage volume V1 when the device is in a substantially vertical position, and each wall is configured such as to define a fluid storage volume (V2 and V3 respectively) in the cavity when the device is in a substantially horizontal position, each of the volumes V2 and V3 being at least equal to the volume V1.

公开(公告)号：US10252807B2

公开(公告)日：2019-04-09

申请号：US15205446

申请日：2016-07-08

申请人： Goodrich Corporation

发明人： Tommy M. Wilson, Jr.

IPC分类号： B64D15/16 ,  B64C1/14 ,  B64C3/00 ,  B64C5/00 ,  B64C11/00 ,  B64C39/12 ,  B64D15/12 ,  B64D29/00 ,  B64D15/00

摘要： An ice protection system includes an aircraft surface and a gutter defined in the aircraft surface between raised rails. The gutter includes a mouth that narrows into a trailing portion of the gutter. The mouth is configured to channel water runback rivulets into the trailing portion of the gutter. The gutter can be a first gutter of a plurality of side by side gutters, each including a respective mouth narrowing into a respective trailing portion, wherein the gutters are separated from one another by respective rails.

公开(公告)号：US10252790B2

公开(公告)日：2019-04-09

申请号：US15234055

申请日：2016-08-11

申请人： General Electric Company

发明人： Kishore Ramakrishnan

IPC分类号： B64C21/06 ,  B64D29/00 ,  F02K3/062 ,  F04D19/00 ,  F04D29/52 ,  F04D29/54 ,  F02K5/00 ,  F02C7/042 ,  B64D33/02

摘要： The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members, such as struts or strakes, mounted at predetermined locations around a circumference of the fan shaft of the fan at the inlet. The predetermined location(s) may be determined as a function of swirl distortion entering the inlet. As such, the structural member(s) are configured to reduce swirl distortion of the airflow entering the fan. In some embodiments, the inlet assembly may also include inlet guide vanes. In alternative embodiments, the inlet assembly may be absent of inlet guide vanes.

公开(公告)号：US20180334249A1

公开(公告)日：2018-11-22

申请号：US15596556

申请日：2017-05-16

申请人： Rohr, Inc.

发明人： Alan J. Binks

IPC分类号： B64C23/06 ,  B64D29/00

CPC分类号： B64C23/06 ,  B64D29/00

摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle exterior skin and a strake. The strake is configured with a base and an airfoil that projects out from the base. The base is recessed into and connected to the nacelle exterior skin.

公开(公告)号：US10093436B2

公开(公告)日：2018-10-09

申请号：US15191143

申请日：2016-06-23

申请人： General Electric Company

发明人： Selaka Bandara Bulumulla ,  Michael Joseph Dell'Anno ,  William Chester Platt

IPC分类号： B64F5/60 ,  G07C5/00 ,  B64D29/06 ,  B64C7/02 ,  B64D29/00 ,  B64D29/08 ,  G05B23/00 ,  B64D45/00

摘要： An engine communication system for aircraft engines having a nacelle with two cowlings extending annularly about the aircraft engine and defining a radially outward surface thereof, and at least one sensor positioned radially inward from the nacelle. The system includes a cowling gap positioned between the two cowlings when coupled together, and an engine control device communicatively coupled to the sensor and configured to at least one of receive engine data from the sensor and receive instruction data from a transmitter device positioned radially outward from the cowling gap. The system also includes a linearly polarized antenna communicatively coupled to the engine control device and positioned radially inward from the cowling gap and extending radially outward toward the cowling gap. The antenna is configured to at least one of receive and transmit the engine data and the instruction data through the cowling gap.

公开(公告)号：US20180230908A1

公开(公告)日：2018-08-16

申请号：US15398375

申请日：2017-01-04

申请人： Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

发明人： Kenneth M. Pesyna ,  Douglas J. Snyder ,  Patrick C. Sweeney

IPC分类号： F02C7/141 ,  F01D25/12 ,  F02C7/18 ,  B64D27/16 ,  B64D29/00 ,  F01D17/14 ,  B64D33/08 ,  B64D33/02

CPC分类号： F02C7/141 ,  B64D27/16 ,  B64D29/00 ,  B64D33/08 ,  B64D2033/024 ,  F01D17/145 ,  F01D25/12 ,  F02C7/14 ,  F02C7/185 ,  F02K3/115 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/606 ,  Y02T50/675

摘要： A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

公开(公告)号：US10040560B2

公开(公告)日：2018-08-07

申请号：US14870401

申请日：2015-09-30

申请人： The Boeing Company

发明人： Robert H. Willie ,  Paul R. Tretow ,  David F. Cerra

IPC分类号： B64D33/04 ,  B64D27/12 ,  B64D29/00 ,  F02K1/82 ,  F02K3/04 ,  F01D25/26 ,  F02K1/38 ,  F02C7/18

摘要： A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.

公开(公告)号：US10017238B2

公开(公告)日：2018-07-10

申请号：US15039003

申请日：2014-11-25

申请人： SNECMA

发明人： Alexandre Leon ,  Julien Pavillet ,  Julien Sayn-Urpar

IPC分类号： B64C1/14 ,  B64D29/00 ,  F01D25/32 ,  F02C7/30 ,  G01L7/00

CPC分类号： B64C1/1453 ,  B64D29/00 ,  F01D25/32 ,  F02C7/30 ,  F05D2220/323 ,  G01L7/00 ,  Y10T137/2012

摘要： Stub for discharging drained fluids for a propulsion unit. The stub includes a cavity for storing the drained fluids and at least one orifice for discharging the fluids contained in the storage cavity, and elements for measuring a difference in pressure outside the stub and a member for draining the storage cavity. The member is able to move between a first position of closing the discharge orifice and a second position of releasing the orifice, and is configured so as to move from the first to the second position when the difference in pressure is greater than, or equal to, a predetermined value.