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公开(公告)号：US20180094645A1
公开(公告)日：2018-04-05
申请号：US15685038
申请日：2017-08-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Timothy Gentry , Richard David Conner
CPC classification number: F04D29/544 , F01D5/141 , F01D11/005 , F01D17/162 , F04D29/563 , F05D2240/121 , F05D2250/70 , Y02T50/673
Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root, thereby forming a locally swept root of the leading edge thereat. The button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
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公开(公告)号：US09920691B2
公开(公告)日：2018-03-20
申请号：US14611316
申请日：2015-02-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael Thomas Tall, Jr. , Brian C. Lund , Jianming Huang
CPC classification number: F02C7/047 , F01D17/162 , F01D25/02 , F04D29/563 , F05D2240/121 , F05D2250/611
Abstract: A manifold for a gas turbine engine includes oppositely facing first and second walls that extend from an annular wall. An undulating wall oppositely faces the annular wall and couples the first wall to the second wall. The walls collectively form a plurality of first chambers in fluid communication with a plurality of second chambers so that each of the second chambers intersperse adjacent first chambers. Each first chamber has a first volume that is greater that a second volume of each second chamber.
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公开(公告)号：US20180051631A1
公开(公告)日：2018-02-22
申请号：US15784463
申请日：2017-10-16
Applicant: United Technologies Corporation
Inventor： Brent Veiga
CPC classification number: F02C7/20 , F01D5/143 , F01D5/145 , F01D9/041 , F01D25/24 , F01D25/28 , F05D2240/121 , Y02T50/673
Abstract: A gas turbine engine nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core casing defined about an axis; a fan nacelle mounted at least partially around the core nacelle; and a support structure extending radially from the core nacelle to the fan nacelle, wherein the support structure has a leading edge that is swept.
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14.发明申请公开(公告)号：US20180045205A1
公开(公告)日：2018-02-15
申请号：US15234029
申请日：2016-08-11
Applicant: General Electric Company
Inventor： Jixian Yao
CPC classification number: F04D27/002 , B64C21/06 , B64C2230/04 , B64D29/00 , F02C7/042 , F02K3/062 , F02K5/00 , F04D19/002 , F04D29/053 , F04D29/522 , F04D29/544 , F05D2220/323 , F05D2240/12 , F05D2240/121 , F05D2240/20 , F05D2240/60
Abstract: The present disclosure is directed to an aerodynamic inlet guide vane assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet guide vane assembly is configured for mounting to fan shaft and a nacelle of the aft fan. The inlet guide vane assembly includes a plurality of inlet guide vanes grouped into a plurality of inlet guide vane groups. Each of the inlet guide vanes has a shape and an orientation corresponding to airflow conditions entering the fan. Further, the inlet guide vane groups are spaced circumferentially around the central axis as a function of the airflow conditions entering the fan.
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公开(公告)号：US09863439B2
公开(公告)日：2018-01-09
申请号：US14483571
申请日：2014-09-11
Applicant: Hamilton Sundstrand Corporation
Inventor： Seth E. Rosen , David A. Dorman , Craig M. Beers
CPC classification number: F04D29/681 , F04D29/444 , F05D2240/121 , F05D2250/52 , F05D2270/101
Abstract: An annular backing plate for a diffuser in a centrifugal compressor comprises an inner diameter and an outer diameter disposed radially opposite the inner diameter. The backing plate also includes a first surface extending between the inner diameter and the outer diameter of the backing plate. A step is formed on the first surface proximate the inner diameter, wherein the step shifts a portion of the first surface encompassed by the step axially aft relative a portion of the first surface not encompassed by the step.
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Patent Agency Ranking
公开(公告)号：US20170335700A1
公开(公告)日：2017-11-23
申请号：US15159935
申请日：2016-05-20
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Brett Alan Bartling
CPC classification number: F01D9/041 , F01D5/18 , F01D9/065 , F05D2220/32 , F05D2230/10 , F05D2230/232 , F05D2230/237 , F05D2240/10 , F05D2240/121 , F05D2240/81 , F05D2250/324 , F05D2260/202
Abstract: A stator for a gas turbine engine includes a stator vane, a first cooling passage located at the stator to provide a cooling fluid flow to a first portion of the stator, and a second cooling passage located at the stator to provide a cooling fluid flow to a second portion of the stator. A connection passage extends at least partially through the stator to connect a first cooling passage inlet of the first cooling passage to a second cooling passage inlet of the second cooling passage. The cooling fluid flow is directed from a common cooling flow source into the first cooling passage and the second cooling passage via the first cooling passage inlet.
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公开(公告)号：US09790861B2
公开(公告)日：2017-10-17
申请号：US14430798
申请日：2013-02-13
Applicant: United Technologies Corporation
Inventor： Brent Veiga
CPC classification number: F02C7/20 , F01D5/143 , F01D5/145 , F01D9/041 , F01D25/24 , F01D25/28 , F05D2240/121 , Y02T50/673
Abstract: A gas turbine engine nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core casing defined about an axis; a fan nacelle mounted at least partially around the core nacelle; and a support structure extending radially from the core nacelle to the fan nacelle, wherein the support structure has a leading edge that is swept.
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公开(公告)号：US09784285B2
公开(公告)日：2017-10-10
申请号：US14485163
申请日：2014-09-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Timothy Gentry , Richard David Conner
CPC classification number: F04D29/544 , F01D5/141 , F01D11/005 , F01D17/162 , F04D29/563 , F05D2240/121 , F05D2250/70 , Y02T50/673
Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
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公开(公告)号：US20170226865A1
公开(公告)日：2017-08-10
申请号：US15040582
申请日：2016-02-10
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Trevor Howard Wood , Dong-Jin Shim , Pranav Dhoj Shah
CPC classification number: F01D5/141 , F01D5/147 , F01D5/282 , F01D5/288 , F01D9/041 , F05D2220/323 , F05D2240/121 , F05D2240/303 , F05D2250/184 , F05D2250/29 , F05D2300/10 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.
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公开(公告)号：US20170211400A1
公开(公告)日：2017-07-27
申请号：US15410540
申请日：2017-01-19
Applicant: SAFRAN AERO BOOSTERS S.A.
Inventor： Frédéric Vallino
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D5/16 , F01D25/02 , F05D2220/323 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2300/501 , F05D2300/505 , Y02T50/673
Abstract: Stator vane for a turbine engine and including at least one portion made from material suitable for superelasticity. The portion made from material suitable for superelasticity is arranged so as to start to resonate at a predetermined speed of the turbine engine, in particular during a speed of the turbine engine typical of the cruising phase of the aircraft.
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