公开(公告)号：US08992081B2

公开(公告)日：2015-03-31

申请号：US13161899

申请日：2011-06-16

申请人： Peter Ireland ,  Andrew Wilson ,  Steven Thorpe ,  Damian Martin

发明人： Peter Ireland ,  Andrew Wilson ,  Steven Thorpe ,  Damian Martin

IPC分类号： G01K7/02 ,  G01K1/14 ,  G01K1/08 ,  G01K13/02

CPC分类号： G01K13/02 ,  G01K13/028

摘要： A high temperature measurement probe comprises an elongate probe body having a measuring head which in use is located in a hot fluid flow. The probe further comprises a thermocouple extending along the interior of the probe body to terminate at a temperature-sensing thermocouple junction inside the measuring head. The probe body has internal passages for circulation of a coolant fluid therein. The measuring head contains a channel, one end of the channel forming an inlet for receiving hot fluid from the hot fluid flow and another end of the channel forming an outlet for discharging the hot fluid received at the inlet. Between the inlet and the outlet a section of the channel extends along the length direction of the probe body. The thermocouple runs along the section of the channel with the thermocouple junction proximate the upstream end of the section.

摘要翻译： 高温测量探头包括具有测量头的细长探针体，测量头在使用中位于热流体流中。 探头还包括沿着探针本体的内部延伸的热电偶，以终止于测量头内的温度感测热电偶结。 探针体具有用于在其中循环冷却剂流体的内部通道。 测量头包含通道，通道的一端形成用于从热流体流接收热流体的入口，并且通道的另一端形成用于排出在入口处接收的热流体的出口。 在入口和出口之间，通道的一部分沿探头主体的长度方向延伸。 热电偶沿着通道的部分延伸，热电偶接头靠近该部分的上游端。

公开(公告)号：US07717668B2

公开(公告)日：2010-05-18

申请号：US11583068

申请日：2006-10-19

申请人： Changmin Son ,  Peter Ireland ,  Steven Thorpe ,  Terence Jones

发明人： Changmin Son ,  Peter Ireland ,  Steven Thorpe ,  Terence Jones

IPC分类号： F01D25/00

CPC分类号： G01M15/14 ,  F05B2230/50 ,  F05B2260/80

摘要： A gas turbine engine simulator comprising a simulator rotor disc which has substantially the same maximum external dimensions as a rotor disc and is manufactured from a material which has a density of less than 220 kg/m3. The simulator rotor disc is manufactured from a foamed plastic material with a closed cell structure. The simulator rotor disc is provided with a cavity in flow communication with a source of simulator coolant fluid, at least one flow outlet, at least one heater unit and at least one thermocouple mounted within said cavity for the measurement of simulator coolant fluid temperature within said cavity.

摘要翻译： 一种燃气涡轮发动机模拟器，其包括模拟器转子盘，其具有与转子盘基本上相同的最大外部尺寸，并且由密度小于220kg / m 3的材料制成。 模拟器转子盘由具有闭孔结构的发泡塑料制成。 模拟器转子盘设置有与模拟器冷却剂流体源，至少一个流出口，至少一个加热器单元和安装在所述腔内的至少一个热电偶流动连通的空腔，用于测量所述腔内的模拟器冷却剂流体温度 腔。

公开(公告)号：US20070207039A1

公开(公告)日：2007-09-06

申请号：US11583068

申请日：2006-10-19

申请人： Changmin Son ,  Peter Ireland ,  Steven Thorpe ,  Terence Jones

发明人： Changmin Son ,  Peter Ireland ,  Steven Thorpe ,  Terence Jones

IPC分类号： F01D5/30

CPC分类号： G01M15/14 ,  F05B2230/50 ,  F05B2260/80

摘要： A gas turbine engine simulator comprising a simulator rotor disc which has substantially the same maximum external dimensions as a rotor disc and is manufactured from a material which has a density of less than 220 kg/m3. The simulator rotor disc is manufactured from a foamed plastic material with a closed cell structure. The simulator rotor disc is provided with a cavity in flow communication with a source of simulator coolant fluid, at least one flow outlet, at least one heater unit and at least one thermocouple mounted within said cavity for the measurement of simulator coolant fluid temperature within said cavity.

摘要翻译： 一种燃气涡轮发动机模拟器，其包括具有与转子盘基本上相同的最大外部尺寸的模拟器转子盘，并且由密度小于220kg / m 3的材料制造。 模拟器转子盘由具有闭孔结构的发泡塑料制成。 模拟器转子盘设置有与模拟器冷却剂流体源，至少一个流出口，至少一个加热器单元和安装在所述腔内的至少一个热电偶流动连通的空腔，用于测量所述腔内的模拟器冷却剂流体温度 腔。

公开(公告)号：US08714918B2

公开(公告)日：2014-05-06

申请号：US13177151

申请日：2011-07-06

申请人： Ian Tibbott ,  Peter Ireland ,  Anthony J Rawlinson ,  Lynne H Turner

发明人： Ian Tibbott ,  Peter Ireland ,  Anthony J Rawlinson ,  Lynne H Turner

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。

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。

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。

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.

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

IPC分类号： G05D1/00 ,  B64D43/02

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。

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

CPC分类号： F01D25/12 ,  F01D25/18 ,  F02C7/14 ,  F02C7/18 ,  F02K3/115 ,  F05D2260/22141

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。

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。