公开(公告)号：US11572789B1

公开(公告)日：2023-02-07

申请号：US17454524

申请日：2021-11-11

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Constantinos Ravanis ,  Vincent Paradis ,  Eduardo Hawie ,  Michael Papple ,  Marc-Antoine Mailloux-Labrousse ,  Othmane Leghzaouni ,  Philippe Boyer ,  Jasrobin Grewal

IPC分类号： F01D5/14

摘要： A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

公开(公告)号：US11572790B1

公开(公告)日：2023-02-07

申请号：US17454529

申请日：2021-11-11

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Remo Marini ,  Panagiota Tsifourdaris ,  Nicolas Grivas ,  Daniel Lecuyer ,  Michael Papple ,  Robert Huszar ,  Othmane Leghzaouni ,  Jonathan Dorai ,  Jasrobin Grewal

IPC分类号： F01D5/14 ,  F01D5/28

摘要： A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

公开(公告)号：US11015450B2

公开(公告)日：2021-05-25

申请号：US16441286

申请日：2019-06-14

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Mohammed Ennacer ,  Dan Olaru ,  Jasrobin Grewal ,  Gaetan Girard

IPC分类号： F01D5/14

摘要： A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

公开(公告)号：US10513929B2

公开(公告)日：2019-12-24

申请号：US15692388

申请日：2017-08-31

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Niloofar Moradi ,  Krishan Mohan ,  Panagiota Tsifourdaris ,  Sami Girgis ,  Vincent Paradis ,  Robert Huszar ,  Jasrobin Grewal

IPC分类号： F01D5/14 ,  F01D5/28 ,  F01D15/08

摘要： A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.