公开(公告)号：US20170254210A1

公开(公告)日：2017-09-07

申请号：US15063048

申请日：2016-03-07

Applicant: General Electric Company

Inventor： Ananda Barua ,  Neelesh Nandkumar Sarawate ,  Kenneth Martin Lewis ,  Changjie Sun ,  Yu Xie Mukherjee ,  Sathyanarayanan Raghavan

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F01D11/08 ,  F05D2230/10 ,  F05D2240/307 ,  F05D2250/75

Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.

公开(公告)号：US10458254B2

公开(公告)日：2019-10-29

申请号：US15353101

申请日：2016-11-16

Applicant: General Electric Company

Inventor： Sathyanarayanan Raghavan ,  Neelesh Nandkumar Sarawate ,  Kenneth Martin Lewis ,  Larry Steven Rosenzweig ,  Changjie Sun ,  Ananda Barua

IPC: F01D5/28 ,  C23C4/04 ,  F04D29/38 ,  F01D11/08 ,  C23C4/12 ,  F01D11/12

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.

公开(公告)号：US10385865B2

公开(公告)日：2019-08-20

申请号：US15063089

申请日：2016-03-07

Applicant: General Electric Company

Inventor： Sathyanarayanan Raghavan ,  Neelesh Nandkumar Sarawate ,  Kenneth Martin Lewis ,  Changjie Sun ,  Ananda Barua

IPC: F04D29/16 ,  F04D29/32

Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.

公开(公告)号：US20180135646A1

公开(公告)日：2018-05-17

申请号：US15353101

申请日：2016-11-16

Applicant: General Electric Company

Inventor： Sathyanarayanan Raghavan ,  Neelesh Nandkumar Sarawate ,  Kenneth Martin Lewis ,  Larry Steven Rosenzweig ,  Changjie Sun ,  Ananda Barua

IPC: F04D29/38

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.

公开(公告)号：US20170254340A1

公开(公告)日：2017-09-07

申请号：US15063089

申请日：2016-03-07

Applicant: General Electric Company

Inventor： Sathyanarayanan Raghavan ,  Neelesh Nandkumar Sarawate ,  Kenneth Martin Lewis ,  Changjie Sun ,  Ananda Barua

IPC: F04D29/32

CPC classification number: F04D29/324 ,  F04D29/164

Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.