19-02-2015 дата публикации
Номер: US20150050158A1
Автор:
David J. Thomas,
Richard C. Uskert,
Adam L. Chamberlain,
Matthew Peter Basiletti,
THOMAS DAVID J,
USKERT RICHARD C,
CHAMBERLAIN ADAM L,
BASILETTI MATTHEW PETER,
THOMAS DAVID J.,
USKERT RICHARD C.,
CHAMBERLAIN ADAM L.
Принадлежит:
A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel. 1. A method of producing a gas turbine engine component comprisingforming a blade from a ceramic matrix composite material, the blade including a blade portion and an engagement portion,bonding at least one compliant layer to the engagement portion, andprocessing the at least one compliant layer to provide a mating surface for engagement with a wheel.2. The method of claim 1 , wherein the blade portion includes a first end and a second end claim 1 , the engagement portion includes a first surface and a second surface coupled to the second end of the blade portion on opposing sides thereof and arranged to extend divergently away from one another claim 1 , and bonding the at least one compliant layer to the engagement portion includes positioning the first surface of the engagement portion in a processing orientation and applying a metallic material to the first surface to form a first compliant layer.3. The method of claim 2 , wherein bonding the at least one compliant layer further includes positioning the second surface of the engagement portion in a processing orientation and applying a metallic material to the second surface to form a second compliant layer.4. The method of claim 3 , wherein the metallic material of the first and second compliant layers is formed into a strip and applied using one of brazing claim 3 , electroless deposition claim 3 , spray coating claim 3 , chemical vapor deposition claim 3 , or plasma spraying.5. The method of claim 3 , wherein the metallic material of the first and second compliant layers is ...
Подробнее
