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公开(公告)号：US20200332666A1
公开(公告)日：2020-10-22
申请号：US16700017
申请日：2019-12-02
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , Darrell Glenn Senile , John Calhoun
Abstract: Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.
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公开(公告)号：US11598216B2
公开(公告)日：2023-03-07
申请号：US16700017
申请日：2019-12-02
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , Darrell Glenn Senile , John Calhoun
IPC: F01D5/18 , F01D5/14 , F01D5/28 , B28B23/00 , B32B37/14 , B32B38/10 , B32B38/08 , B32B38/00 , F01D9/04 , F01D25/00 , F01D25/12
Abstract: Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.
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公开(公告)号：US10605095B2
公开(公告)日：2020-03-31
申请号：US15151860
申请日：2016-05-11
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , Darrell Glenn Senile , John Calhoun
Abstract: Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.
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公开(公告)号：US20170328217A1
公开(公告)日：2017-11-16
申请号：US15151860
申请日：2016-05-11
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , Darrell Glenn Senile , John Calhoun
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/284 , F01D5/288 , F01D9/041 , F01D25/005 , F01D25/12 , F05D2220/32 , F05D2230/50 , F05D2230/90 , F05D2260/202 , F05D2260/204 , F05D2300/6033 , F05D2300/611 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.
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