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US 2026/0266187 A1Published application
Gas turbine engine static vane clusters
AssigneeRtx Corporation
InventorChristian X. Campbell
Life of this patent
Estimating the term…
Abstract
A multiple static vane component includes a plurality of airfoils each formed of ceramic matrix composite materials. Each of the airfoils are attached to an inner platform and an outer platform both formed of ceramic matrix composite materials. There is a plurality of individual parts forming the plurality of airfoils, the inner platform or the outer platform, bonded to each other with a braze joint. A gas turbine engine and a method are also disclosed.
Claims20
A multiple static vane component comprising:
- a plurality of airfoils each formed of ceramic matrix composite materials, and each of said airfoils attached to an inner platform and an outer platform both formed of ceramic matrix composite materials, and there being a plurality of individual parts forming the plurality of airfoils, the inner platform or the outer platform, bonded to each other with a braze joint.
A gas turbine engine comprising:
- a compressor connected to a combustor, the combustor connected to a turbine section, the turbine section having a plurality of turbine rows spaced along an axis of rotation of the turbine rotor, and there being at least one vane row intermediate axially spaced ones of said turbine blade rows;
- and
- the at least one vane row having a plurality of airfoils each formed of ceramic matrix composite materials, and each of said airfoils attached to an inner platform and an outer platform both formed of ceramic matrix composite materials, and there being a plurality of individual parts forming the plurality of airfoils, the inner platform or the outer platform, bonded to each other with a braze joint.
A method of forming a static vane comprising the steps of:
- (1) forming an airfoil from ceramic matrix composites having a leading edge and a trailing edge;
- (2) separately forming an inner and outer platform from ceramic matrix composites;
- and
- (3) performing at least one of drilling a hole into the airfoil or applying a coating to the airfoil;
- then (4) brazing the radially inner and outer platforms to the airfoil.
2 more elements
Dependencies are inferred from the claim text.