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公开(公告)号：US20050074325A1
公开(公告)日：2005-04-07
申请号：US10946105
申请日：2004-09-22
CPC分类号： F01D5/18 , F05D2260/201 , F05D2260/221 , F23R3/04 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by impingement of the coolant flow upon a surface 7 to be cooled is improved. Typically, a plurality of jets 1 are provided in a housing wall 8. These jets 1 will be arranged in an appropriate pattern to achieve cooling by flow impingement upon the surface 7 to be cooled. Possibly, a plurality of jets 1 in an appropriate pattern may be arranged upstream of conventional circular coolant jets in order to provide some protection for those circular coolant jets from lateral or cross flow.
摘要翻译： 冷却喷嘴1设置有大于宽度3的纵向方面2.因此，流过喷嘴1的冷却剂流不易受到呈现给该冷却剂流的横向或横向流动的偏转，使得冷却剂的冷却剂流动到 要冷却的表面7得到改善。 通常，多个喷射器1设置在壳体壁8中。这些喷射器1将被布置成适当的图案，以通过流动冲击来冷却待冷却的表面7上的冷却。 可能地，可以将多个适当图案的喷嘴1布置在传统的圆形冷却剂喷流的上游，以便为这些圆形冷却剂喷嘴提供一些保护以防止横向或横向流动。
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公开(公告)号：US07585152B2
公开(公告)日：2009-09-08
申请号：US10946105
申请日：2004-09-22
CPC分类号： F01D5/18 , F05D2260/201 , F05D2260/221 , F23R3/04 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by impingement of the coolant flow upon a surface 7 to be cooled is improved. Typically, a plurality of jets 1 are provided in a housing wall 8. These jets 1 will be arranged in an appropriate pattern to achieve cooling by flow impingement upon the surface 7 to be cooled. Possibly, a plurality of jets 1 in an appropriate pattern may be arranged upstream of conventional circular coolant jets in order to provide some protection for those circular coolant jets from lateral or cross flow.
摘要翻译： 冷却喷嘴1设置有大于宽度3的纵向方面2.因此，流过喷嘴1的冷却剂流不易受到呈现给该冷却剂流的横向或横向流动的偏转，使得冷却剂的冷却剂流动到 要冷却的表面7得到改善。 通常，多个喷射器1设置在壳体壁8中。这些喷射器1将被布置成适当的图案，以通过流动冲击来冷却待冷却的表面7上的冷却。 可能地，可以将多个适当图案的喷嘴1布置在传统的圆形冷却剂喷流的上游，以便为这些圆形冷却剂喷嘴提供一些保护以防止横向或横向流动。
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公开(公告)号：US20100034638A1
公开(公告)日：2010-02-11
申请号：US11056185
申请日：2005-02-14
IPC分类号： F02C7/12
CPC分类号： F01D25/12 , F01D5/187 , F05D2250/231 , F05D2250/292 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/673 , Y02T50/675 , Y02T50/676
摘要： An impingement cooling arrangement comprises a projection extending partially across a coolant passage upstream of a jet aperture. An end surface of the projection increases the available surface area for heat exchange with a cross flow whilst a coolant air flow jetted from the jet aperture can transgress a proportion of the air flow passing between the end surface and a junction surface incorporating the jet aperture. A spacing gap B between the end surface and the junction surface avoids localised distortions to the cross flow whilst the projection provides that the coolant air flow projected from the jet aperture mostly passes through a lower turbulence wake downstream of the projection for greater impingement upon a target surface for heat transfer and cooling efficiency. Typically the impingement cooling arrangement is incorporated within turbine blades or vanes of a jet engine.
摘要翻译： 冲击冷却装置包括部分地穿过喷射孔上游的冷却剂通道延伸的突出部。 突起的端面增加了用于与横流进行热交换的可用表面积，而从喷射孔喷射的冷却剂空气流可以超过在端表面和结合有喷射孔的接合面之间通过的一部分空气流。 端表面和接合表面之间的间隔间隙B避免了横向流动的局部变形，同时突出部分提供从喷射孔径突出的冷却剂空气流大部分通过突出部下游的下部湍流尾迹，以便更大程度地撞击目标 表面用于传热和冷却效率。 通常，冲击冷却装置结合在喷气发动机的涡轮机叶片或叶片内。
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公开(公告)号：US08714918B2
公开(公告)日：2014-05-06
申请号：US13177151
申请日：2011-07-06
IPC分类号： F01D11/10
CPC分类号： F01D11/08 , F01D11/10 , F01D11/24 , F01D25/12 , F05D2240/11 , F05D2250/313 , F05D2250/314 , F05D2260/202 , Y02T50/676 , Y10T29/49323
摘要： A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use a leakage flow of the working gas passes through the clearance gap between the blade tips and the segment. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air opposes the leakage flow of the working gas.
摘要翻译： 用于燃气涡轮发动机的涡轮级的护罩段形成用于工作台的工作气体环的端壁。 该段还提供了跨越段的一排涡轮机叶片的尖端的紧密间隙。 在使用中，工作气体的泄漏流通过叶片尖端和段之间的间隙。 该段具有用于冷却孔的多个冷却孔和各自的空气供给通道。 冷却孔分布在由叶片尖端扫过的段的气体洗涤表面的那部分上。 冷却孔在使用中提供散布在气洗表面上的冷却空气。 供给通道构造成使得所输送的空气与工作气体的泄漏流相反。
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公开(公告)号：US20140050581A1
公开(公告)日：2014-02-20
申请号：US13940241
申请日：2013-07-11
申请人： Peter Ireland
发明人： Peter Ireland
IPC分类号： F01D5/28
CPC分类号： F01D5/286 , B64C3/26 , B64C11/205 , B64C27/473 , F03D1/0675 , Y02E10/721 , Y02T50/673
摘要： An erosion protection system and method applicable to foils or aerodynamic surfaces. Single element erosion protective elements having joggles are provided, each single element being alignable with the next to provide a contiguous erosion protection layer.
摘要翻译： 适用于箔片或空气动力学表面的侵蚀保护系统和方法。 提供具有滑块的单元侵蚀保护元件，每个单个元件可与下一个元件对准，以提供连续的侵蚀保护层。
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公开(公告)号：US20070010947A1
公开(公告)日：2007-01-11
申请号：US11176042
申请日：2005-07-07
申请人： Peter Ireland , James Thornton , Gregory Wibben , Kamran Waheed , Stephen Reski
发明人： Peter Ireland , James Thornton , Gregory Wibben , Kamran Waheed , Stephen Reski
IPC分类号： G01V1/40
CPC分类号： G01V1/40
摘要： Techniques for generating deliverable files from well logging data include obtaining the well logging data, wherein the well logging data is associated with a unique identifier; outputting a graphical deliverable file based on the well logging data, one or more templates, and a set of graphical deliverable attributes that specify how the graphical deliverable file is to be generated; and outputting an electronic data file comprising the set of graphical deliverable attributes such that the graphical deliverable file can be regenerated from the electronic data file. The well logging data may include all information necessary to recalculate the computed outputs from the raw data (e.g., computational parameters). Other methods include techniques for uniquely associating data and for making the outputs tamper-proof so that a user can compare two different types of outputs (e.g., digital and graphical deliverables) and be confident whether they are from the same source data.
摘要翻译： 从测井数据生成可交付文件的技术包括获得测井数据，其中测井数据与唯一标识符相关联; 基于测井数据，一个或多个模板以及指定如何生成图形可交付文件的一组图形可交付属性输出图形可交付文件; 以及输出包括所述一组图形可交付属性的电子数据文件，使得可以从电子数据文件再生图形可交付文件。 测井数据可以包括从原始数据重新计算计算的输出所需的所有信息（例如，计算参数）。 其他方法包括用于唯一地关联数据和使输出防篡改的技术，使得用户可以比较两种不同类型的输出（例如，数字和图形可交付物），并且确定它们是否来自相同的源数据。
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公开(公告)号：US20170137116A1
公开(公告)日：2017-05-18
申请号：US15319807
申请日：2014-06-24
申请人： Peter Ireland , Anthony Ireland
发明人： Peter Ireland , Anthony Ireland
IPC分类号： B64C23/06 , B64C21/10 , F04D29/32 , F01D9/02 , F23R3/00 , F04D27/00 , F01D5/14 , B64F5/60 , F04D29/54
CPC分类号： B64C23/06 , B64C21/10 , B64C2230/26 , F01D5/145 , F01D5/147 , F04D29/324 , F04D29/542 , F04D29/681 , F05D2240/127 , F05D2250/182 , F05D2250/183 , F15D1/003 , F15D1/12 , F23R3/002 , Y02T50/162 , Y02T50/166 , Y02T50/672 , Y02T50/673
摘要： Methods and related apparatus embodiments are disclosed that allow novel Conformal Vortex Generator and/or Elastomeric Vortex Generator art to improve energy efficiency and control capabilities at many surface points of a body or object moving at speed in aero/hydrodynamic Newtonian fluids, by reducing; shock energy losses, surface flow turbulence, and/or momentum layer thicknesses.
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公开(公告)号：US20160357182A1
公开(公告)日：2016-12-08
申请号：US15175030
申请日：2016-06-06
申请人： Peter Ireland
发明人： Peter Ireland
CPC分类号： G05D1/0005 , B64D43/02
摘要： An aircraft planning control system and method. According to one embodiment, a flight management computer and remote server system are communicably coupled to a plurality of sensors, the plurality of sensors recording data associated with an aircraft in operation. The data is used by the remote server system and flight management computer to generate real-time performance data for the aircraft, and to optimize a speed schedule for the aircraft.
摘要翻译： 飞机规划控制系统及方法。 根据一个实施例，飞行管理计算机和远程服务器系统可通信地耦合到多个传感器，所述多个传感器记录与正在运行的飞行器相关联的数据。 数据由远程服务器系统和飞行管理计算机用于生成飞机的实时性能数据，并优化飞机的速度计划。
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公开(公告)号：US08721271B2
公开(公告)日：2014-05-13
申请号：US12956501
申请日：2010-11-30
申请人： Yi Wang , Miles T Trumper , Mark J Wilson , Peter Ireland , Robert C Chambers
发明人： Yi Wang , Miles T Trumper , Mark J Wilson , Peter Ireland , Robert C Chambers
IPC分类号： F01D5/08
摘要： An air-cooled oil cooler for the wall of an air flow passage of a gas turbine engine is provided, the oil cooler allowing improved heat exchange performance to be obtained. This is achieved by: (I) diverting air flow from the inner side of the oil cooler towards the outer side of the oil cooler, (ii) enhancing heat exchange performance at the leading edge of the cooler, and/or (iii) suppressing airflow wake at the trailing edge of the cooler.
摘要翻译： 提供了一种用于燃气涡轮发动机的空气流动通道的壁的风冷式油冷却器，能够获得改善的热交换性能的油冷却器。 这通过以下方式实现：（I）将空气流从油冷却器的内侧转向油冷却器的外侧，（ii）提高冷却器前缘处的热交换性能，和/或（iii）抑制 气流在冷却器的后缘处醒来。
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公开(公告)号：US20110008174A1
公开(公告)日：2011-01-13
申请号：US12832966
申请日：2010-07-08
申请人： Peter Ireland
发明人： Peter Ireland
IPC分类号： F04D29/38
CPC分类号： B64C23/06 , B64C23/065 , B64C2003/147 , Y02T50/12 , Y02T50/162 , Y02T50/164
摘要： A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been problematic from engineering and cost considerations. A novel and efficient vortex generator profile is identified, which develops an additional co rotating vortex at low energy expenditure. The mechanisms allow for the application of transverse vortex generators, or Gurney Flaps/Lift Enhancement Tabs/Divergent Trailing Edges, to propellers, rotorblades, and to wings/flaps/control trailing edges. Cove Tabs are additionally described using an elastomeric transverse vortex generator to achieve performance improvements of a high lift device.
摘要翻译： 通过应用保形弹性涡流发生器来改善箔的空气动力学性能的方法。 弹性体的新颖使用允许将各种形式的涡流发生器应用于从工程和成本考虑问题的部分。 确定了一种新颖有效的涡流发生器轮廓，其在低能量消耗下产生额外的共旋转涡流。 这些机构允许将横向涡流发生器或Gurney襟翼/升力增强翼片/发散尾翼边缘应用于螺旋桨，转子叶片以及翼/翼/控制后缘。 使用弹性体横向涡流发生器另外描述了小翼片，以实现高提升装置的性能改进。
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