公开(公告)号：US20210062673A1

公开(公告)日：2021-03-04

申请号：US16551161

申请日：2019-08-26

申请人： PRATT & WHITNEY CANANDA CORP.

发明人： Martin DROLET ,  Melanie BRILLANT

IPC分类号： F01D17/08 ,  G01K13/02

摘要： A method and system for monitoring a temperature of a gas turbine engine are described. The method comprises obtaining individual sensor readings from functioning temperature sensors of a sensor array, where a number of the functioning temperature sensors is less than a total number of temperature sensors in the sensor array; applying correction factors to the individual sensor readings of the functioning temperature sensors based on deviations of the individual sensor readings from a total average temperature of all the temperature sensors in the array, to obtain corrected individual sensor readings; and determining a corrected total average temperature as a sum of the corrected individual sensor readings divided by the number of functioning temperature sensors.

公开(公告)号：US10145301B2

公开(公告)日：2018-12-04

申请号：US14493758

申请日：2014-09-23

申请人： Pratt & Whitney Cananda Corp.

发明人： Farid Abrari ,  Peter Townsend

IPC分类号： F01D25/04 ,  F02C7/055 ,  F02K3/06

摘要： An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.

公开(公告)号：US20160084162A1

公开(公告)日：2016-03-24

申请号：US14493758

申请日：2014-09-23

申请人： Pratt & Whitney Cananda Corp.

发明人： Farid ABRARI ,  Peter TOWNSEND

IPC分类号： F02C7/055

CPC分类号： F02C7/055 ,  F02K3/06 ,  F05D2240/307 ,  F05D2250/182 ,  F05D2250/51 ,  F05D2250/71

摘要： An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.

摘要翻译： 涡扇发动机的入口，包括围绕入口流动路径的入口壁。 入口壁从上游端轴向延伸到与风扇相邻的下游端。 入口壁具有限定围绕入口周向间隔开的多个齿的形状。 齿沿轴向延伸并朝向中心纵向轴线径向向内突出。 入口流动路径的中心部分具有在相对的齿之间径向测量的横截面尺寸，横截面尺寸沿轴向方向变化。 中心部分以横截面尺寸的最小值限定几何喉部。 入口壁的形状使得几何喉部与上游端和下游端轴向间隔开。 还讨论了燃气涡轮发动机和屏蔽风扇叶片尖端的方法不受具有预定最小尺寸的物体的冲击。