초록 ▼

A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of t

A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.

대표청구항 ▼

1. A method for forming a gas turbine engine airfoil assembly, comprising: providing at least two gas turbine engine airfoil composite preform components,interlocking the airfoil composite preform components with a first locking component, andinterlocking the first locking component and at least one

1. A method for forming a gas turbine engine airfoil assembly, comprising: providing at least two gas turbine engine airfoil composite preform components,interlocking the airfoil composite preform components with a first locking component, andinterlocking the first locking component and at least one of the airfoil composite preform components with a second locking component, andafter interlocking with each of the first and second locking components, rigidizing the assembly of aircraft component preform components, the first locking component, and the second locking component,wherein the airfoil composite preform components comprise an airfoil and an endwall, and the first locking component interlocks the airfoil and the endwall and the second locking component interlocks the first locking component and the endwall, and the second interlocking comprises inserting the second locking component into a through hole in the first locking component and a through hole in the endwall. 2. The method of claim 1, wherein the rigidizing comprises using vapor infiltration. 3. The method of claim 1, wherein one or more of the airfoil composite preform components are provided in a partially rigidized state. 4. The method of claim 1, wherein the airfoil composite preform components comprise woven fiber. 5. A method for forming a gas turbine engine airfoil assembly, comprising: providing at least two gas turbine engine airfoil composite preform components,interlocking the airfoil composite preform components with a first locking component, andinterlocking the first locking component and at least one of the airfoil composite preform components with a second locking component, andafter interlocking with each of the first and second locking components, rigidizing the assembly of aircraft component preform components, the first locking component, and the second locking component,wherein the airfoil composite preform components comprise an airfoil and an endwall, the airfoil including at least one airfoil connecting tab and a seat portion, the endwall defining an opening substantially sized to receive therethrough the at least one airfoil connecting tab, wherein the providing comprises inserting the at least one airfoil connecting tab of the airfoil into the opening of the endwall so that the endwall rests over the seat portion,wherein the seat portion provides a mating face of the airfoil and the portion of the endwall over the seat portion provides a mating face of the endwall, the method further comprising inserting a filler material between the mating face of the airfoil and the mating face of the endwall,wherein the airfoil includes an airfoil body that is hollow, the airfoil body including a body wall comprising a pressure side body wall and a suction side body wall defining a hollow space therebetween, the seat portion defined on an outer end of the body wall. 6. The method of claim 5, wherein the interlocking comprises inserting the first locking component into a through hole in the at least one airfoil connecting tab so that a rear portion of the first locking component rests over a portion of the endwall to interlock the endwall between the first locking component and the seat portion. 7. A gas turbine airfoil assembly, comprising: an endwall composite preform including a platform portion having a receiver opening and an endwall locking slot defined therethrough,an airfoil composite preform including an airfoil body, at least one connecting tab extending from the body into the receiver opening and having an airfoil locking slot defined therethrough, the body defining a seat portion on an outer end engaged with the platform portion as mating faces, andfirst and second locking components, the first locking component extending through the airfoil locking slot to interlock the airfoil preform and the endwall and including a locking hole aligned with the endwall locking slot, the second locking component arranged to extend into each of the locking hole the endwall locking slot to interlock the second locking component with the endwall,wherein the airfoil body is hollow and includes a body wall comprising a pressure side body wall and a suction side body wall defining a hollow space therebetween, the seat portion defined on the outer end of the body. 8. The airfoil assembly of claim 7, wherein the at least one connecting tab extends from the outer end of the body. 9. The airfoil assembly of claim 8, wherein the at least one connecting tab includes at least two connecting tabs, one of which extends from each of the pressure side and suction side body walls. 10. The airfoil assembly of claim 7, wherein at least one of the endwall and the airfoil is partially rigidized. 11. The airfoil assembly of claim 10, wherein at least one of the endwall and the airfoil comprise woven fiber.