-
公开(公告)号：JP2011102588A
公开(公告)日：2011-05-26
申请号：JP2010277639
申请日：2010-12-14
Inventor： LORBER PETER F , LORD WESLEY K
CPC classification number: B64C21/025 , B64C11/18 , B64C27/467 , B64C2230/20 , B64C2230/28 , F01D5/145 , F04D29/682 , F04D29/684 , Y02T50/166 , Y02T50/66 , Y02T50/673 , Y10S415/914
Abstract: PROBLEM TO BE SOLVED: To provide a fan blade capable of improving a flow of a boundary layer. SOLUTION: Blades 37, 38 such as the fan blades of gas turbines comprise air inlets near the hub 39 thereof, respectively. These inlets can be disposed at the pressure side of the blades and/or near front ends of the blades and near tips or the trailing edges thereof, respectively. Air plenums are provided between the air inlets and slots 47, 48, respectively. Air is expedited to flow into the air inlet, flows through the plenums, flows out of the slots, and flows into the flows adjacent to the blades. These slots normally extend through intake surfaces of the blades near positions where boundary layers are separated. Consequently, the air flowing out of the slots flows into the boundary layers of the intake surfaces of the blades, and the start of the separation of the boundary layer is prevented, or an impact of supersonic speed can be alleviated. COPYRIGHT: (C)2011,JPO&INPIT
Abstract translation: 要解决的问题：提供一种能够改善边界层流动的风扇叶片。 解决方案：叶片37,38，例如燃气轮机的风扇叶片分别包括靠近其毂39的空气入口。 这些入口可以分别设置在叶片的压力侧和/或叶片的前端附近以及其附近的尖端或后缘。 空气通风口分别设置在空气入口和槽47,48之间。 空气加速流入进气口，流经气室，流出槽，流入与叶片相邻的流中。 这些槽通常在叶片的进入表面附近靠近边界层分离的位置。 因此，从狭缝流出的空气流入叶片的进气面的边界层，防止了边界层的分离开始，或者可以缓解超音速的冲击。 版权所有（C）2011，JPO＆INPIT
-
2.发明专利Inlet guide vane flap, fan section, and control method for variable-shape inlet guide vane flap system 有权入口指南VANE FLAP，风扇部分和可变形导向导叶片系统的控制方法
公开(公告)号：JP2011132963A
公开(公告)日：2011-07-07
申请号：JP2011083273
申请日：2011-04-05
Inventor： LORD WESLEY K , SHARMA OM P , DYE CHRISTOPHER , SUCIU GABRIEL L
IPC: F04D29/56
CPC classification number: F01D5/146 , F01D5/148 , F01D17/162 , F04D29/563 , F05B2240/311 , F05D2240/12 , Y02T50/673
Abstract: PROBLEM TO BE SOLVED: To provide an inlet guide vane flap with increased partial-speed operability and flutter margin, thus avoiding fan rotor mistuning at particular operational conditions. SOLUTION: A variable-shape inlet guide vane (IGV) system 46 includes the variable-shape inlet guide vane flap 48 provided with a flexible part 64 that enables the desired spanwise distribution of axial velocities Cx, α, and β at an inlet of the fan rotor 30. The flexible part 64 is formed of a flexible material such as silicone rubber combined with internal reinforcing fibers or filaments. The form of the flap 48 is not symmetric, but twisted during actuation from the maximum opening position to the maximum closed position. COPYRIGHT: (C)2011,JPO&INPIT
Abstract translation: 要解决的问题：提供具有增加的部分速度可操作性和颤振余量的入口导向叶片翼片，从而避免在特定操作条件下风扇转子失谐。 解决方案：可变形入口引导叶片（IGV）系统46包括设置有柔性部分64的可变形入口导向叶片翼片48，其能够在轴向速度Cx，α和β处产生期望的翼展方向分布 风扇转子30的入口。柔性部分64由诸如与内部增强纤维或细丝组合的硅橡胶的柔性材料形成。 翼片48的形状不是对称的，而是在从最大打开位置到最大关闭位置的致动期间扭转。 版权所有（C）2011，JPO＆INPIT
-
公开(公告)号：JP2000145475A
公开(公告)日：2000-05-26
申请号：JP24721499
申请日：1999-09-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZYSMAN STEVEN H , LORD WESLEY K , KOHLENBERG GREGORY A
Abstract: PROBLEM TO BE SOLVED: To provide a jet noise suppression system having an enhanced suppression effect for an engine in high power level operation. SOLUTION: This jet noise suppressor for a gas turbine engine has no adverse effect on thrust and performance of an engine. The jet noise suppressor includes a nozzle and is provided with a disposition of tabs 40 arranged at a downstream end of the nozzle. The tabs 40 possess a squarish offset with respect to its length and an engine stream, and cause mixing at the boundary of the engine stream and ambient air. A tab shape which is a trapezoid having tapered side faces 55 reduces any adverse effect on engine performance.
-
4.发明申请
公开(公告)号：WO2014078003A3
公开(公告)日：2014-08-07
申请号：PCT/US2013065337
申请日：2013-10-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , EPSTEIN ALAN H , LORD WESLEY K , CHANDLER JESSE M
CPC classification number: F01D25/08 , F02C7/052 , Y02T50/675
Abstract: A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.
Abstract translation: 燃气涡轮发动机在入口端处包括鼻锥，并且在机舱的径向内侧间隔开。 压缩机位于机头锥体的下游。 一个核心入口将空气锥形下游的空气输送到压缩机中。 入口颗粒分离器包括用于向核心入口径向向外输送空气的歧管。 由入口颗粒分离器输送的空气在通过出口之前通过热交换器。
-
公开(公告)号：WO2014143281A8
公开(公告)日：2014-11-27
申请号：PCT/US2013075955
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LORD WESLEY K , MALECKI ROBERT E
CPC classification number: F02K3/06 , B64D33/04 , B64D2033/0286 , F01D25/24 , F02C3/04 , F02K1/78 , F05D2220/32 , F05D2240/24 , F05D2240/35 , F05D2250/73
Abstract: A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined there between. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.
Abstract translation: 用于飞机燃气涡轮发动机的风扇喷嘴由设置在风扇罩内的核心发动机罩组成，从而在其间限定空气流动区域。 核心发动机罩和风扇罩布置在水平中心平面周围。 风扇罩具有大致圆形形状，并且由具有第一半径的上部基本上半圆形部分和具有第二半径的下部基本上半圆形部分形成。 芯发动机整流罩具有大致圆形形状，并且由具有第三半径的上部大致半圆形部分和具有第三半径的下部基本上半圆形部分形成。 核心发动机罩的上部基本上半圆形的部分包括左弓形件和右弓形件。 第二半径小于第一半径，第三半径小于第四半径。
-
Patent Agency Ranking
公开(公告)号：WO2015134081A3
公开(公告)日：2015-12-30
申请号：PCT/US2014070061
申请日：2014-12-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LORD WESLEY K
CPC classification number: F02C3/04 , B64D27/14 , B64D29/04 , B64D2027/005 , F02C3/10 , F02C3/107 , F02C7/36 , F02K3/025 , F02K3/072 , F05D2220/32 , F05D2220/325 , F05D2250/313 , Y02T50/66 , Y02T50/671
Abstract: The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator power core axis, as well as to the aircraft longitudinal axis.
Abstract translation: 本公开一般涉及具有由燃气涡轮发动机提供动力的反向旋转推动器支柱的飞行器，所述燃气涡轮发动机具有基本上垂直于压缩机，燃烧器和涡轮气体发生器动力核心轴线以及飞机纵向轴线设置的动力涡轮机。
-
7.发明申请GAS TURBINE NACELLE COMPRISING A PASSIVE BOUNDARY LAZER BLEED SYSTEM AND METHOD OF CONTROLLING TURBULENT AIRFLOW 审中-公开包含无源边界喷淋系统的气体涡轮机和控制涡流气流的方法
公开(公告)号：WO2008045051A3
公开(公告)日：2009-06-18
申请号：PCT/US2006039797
申请日：2006-10-12
Applicant: UNITED TECHNOLOGIES CORP , ZYSMAN STEVEN H , LORD WESLEY K , MILLER ROBERT M , ATASSI OLIVER V
Inventor： ZYSMAN STEVEN H , LORD WESLEY K , MILLER ROBERT M , ATASSI OLIVER V
IPC: F02C7/04
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
Abstract: A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.
Abstract translation: 燃气涡轮发动机系统包括具有压力侧和吸力侧的机舱。 通道在压力侧和吸力侧之间延伸，允许从压力侧到吸力侧的气流。 通道在机舱上接收湍流气流，以在通道后面的机舱上方产生层流气流，从而减少机舱上的阻力。
-
公开(公告)号：AU4448900A
公开(公告)日：2000-09-14
申请号：AU4448900
申请日：2000-02-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCORMICK DUANE C , LORD WESLEY K
Abstract: Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with low momentum flux particles drawn from the fluid flow in a direction normal to the surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage.
-
公开(公告)号：DE602005022687D1
公开(公告)日：2010-09-16
申请号：DE602005022687
申请日：2005-06-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHLINKER ROBERT , NARAVANAN SATISH , LORD WESLEY K , KOHLENBERG GREGORY A , REBA RAMONS , SIMONICH JOHN , SOTERIOU MARIOS C , MAEDER THIERRY
-
公开(公告)号：CA2372295A1
公开(公告)日：2000-08-31
申请号：CA2372295
申请日：2000-02-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCORMICK DUANE C , LORD WESLEY K
Abstract: Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle o f which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with l ow momentum flux particles drawn from the fluid flow in a direction normal to t he surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage.
-
-
-
-
-
-
-
-
-
Search Results
36
records
(took 0.027 seconds)
