A gas turbine engine compressor spacer (230) includes a body (229) with a hollow cylinder shape. The body (229) includes an outer surface (232) with an axially forward end. The body (229) also includes a forward face (233) extending radially inward from the axially forward end. A forward lip (237) extends axially from the body (229). The forward lip (237) includes a forward lip surface (239) located radially inward from the forward face (233). The forward lip surface (239) is the radially outer circumferential surface of the forward lip (237). The spacer (230) also includes a forward undercut (235). The forward undercut (235) is located between the forward face (233) and the forward lip surface (239).
申请公布号
US2014064946(A1)
申请公布日期
2014.03.06
申请号
US201213605615
申请日期
2012.09.06
申请人
NIELSEN ENGWARD WILLIAM;HURST KENNETH BLAIR;SIORDIA, II VICTOR MANUEL;SOLAR TURBINES INCORPORATED
发明人
NIELSEN ENGWARD WILLIAM;HURST KENNETH BLAIR;SIORDIA, II VICTOR MANUEL