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公开(公告)号：US09464610B2
公开(公告)日：2016-10-11
申请号：US13747391
申请日：2013-01-22
Applicant: General Electric Company
Inventor： Niraj Kumar Mishra
CPC classification number: F02M53/043 , F02C3/28 , F02M69/04 , F05D2260/20 , Y02E20/16 , Y02E20/18
Abstract: According to various embodiments, a system includes a gasification fuel injector. The gasification fuel injector includes a tip portion, an annular coolant chamber disposed in the tip portion, and a first structural support extending through the annular coolant chamber. The first structural support divides the annular coolant chamber into a first passage and a second passage.
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公开(公告)号：US20180320538A1
公开(公告)日：2018-11-08
申请号：US15589059
申请日：2017-05-08
Applicant: General Electric Company
Inventor： Craig Allen Bielek , Niraj Kumar Mishra
CPC classification number: F01D9/041 , F01D5/141 , F01D5/142 , F01D5/143 , F05D2220/321 , F05D2250/74
Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US20130125859A1
公开(公告)日：2013-05-23
申请号：US13747391
申请日：2013-01-22
Applicant: General Electric Company
Inventor： Niraj Kumar Mishra
CPC classification number: F02M53/043 , F02C3/28 , F02M69/04 , F05D2260/20 , Y02E20/16 , Y02E20/18
Abstract: According to various embodiments, a system includes a gasification fuel injector. The gasification fuel injector includes a tip portion, an annular coolant chamber disposed in the tip portion, and a first structural support extending through the annular coolant chamber. The first structural support divides the annular coolant chamber into a first passage and a second passage.
Abstract translation: 根据各种实施例，系统包括气化燃料喷射器。 气化燃料喷射器包括尖端部分，设置在尖端部分中的环形冷却剂室和延伸穿过环形冷却剂室的第一结构支撑件。 第一结构支撑件将环形冷却剂室分成第一通道和第二通道。
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公开(公告)号：US10408072B2
公开(公告)日：2019-09-10
申请号：US15589059
申请日：2017-05-08
Applicant: General Electric Company
Inventor： Craig Allen Bielek , Niraj Kumar Mishra
Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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