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公开(公告)号：US09995160B2
公开(公告)日：2018-06-12
申请号：US14578816
申请日：2014-12-22
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Kirk D. Gallier , Robert Frederick , Darrell Senile , Benjamin Huizenga
CPC classification number: F01D9/065 , F01D5/282 , F01D5/284 , F01D11/005 , F01D25/162 , F05D2300/6033 , Y02T50/672
Abstract: An airfoil profile-shaped seal is disposable between an inside surface of a hollow airfoil body and a seal support. The seal includes an elongated member defining a generally closed curve having a generally straight portion, a generally curved portion, and having a solid cross-section across and along the length of the elongated member. When the seal is disposed in an airfoil profile-shaped groove of a seal support adjacent to the inner surface of the hollow airfoil body, and a fluid pressure on one side of the seal is greater than a fluid pressure on the other side of the seal, portions of the seal engage the inner surface of the hollow airfoil body and a surface of the groove to form a seal to inhibit leakage of fluid from the one side to the other side.
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公开(公告)号：US10161257B2
公开(公告)日：2018-12-25
申请号：US14887537
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Benjamin Scott Huizenga , Kevin Robert Feldmann , Robert Alan Frederick , Robert Charles Groves, II , Kirk Douglas Gallier , Timothy Francis Andrews , Darrell Senile
Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectively. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.
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公开(公告)号：US20170107837A1
公开(公告)日：2017-04-20
申请号：US14887537
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Benjamin Scott Huizenga , Kevin Robert Feldmann , Robert Alan Frederick , Robert Charles Groves, II , Kirk Douglas Gallier , Timothy Francis Andrews , Darrell Senile
CPC classification number: F01D11/005 , F01D5/284 , F01D9/023 , F01D9/041 , F01D9/047 , F01D25/12 , F05D2220/32 , F05D2240/57 , F05D2250/71 , F05D2300/6033 , F16J15/061 , F16J15/0887 , Y02T50/672
Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.
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