초록 ▼

A gas turbine engine vane assembly provides double impingement cooling of a vane platform. An impingement structure disposed adjacent the vane platform defines at least first and second plenums in fluid flow communication, respectively defined in part by the vane platform. The vane platform has firs

A gas turbine engine vane assembly provides double impingement cooling of a vane platform. An impingement structure disposed adjacent the vane platform defines at least first and second plenums in fluid flow communication, respectively defined in part by the vane platform. The vane platform has first and second surfaces defined within the first and second plenums, and which are cooled by successive impingement of secondary cooling air flow through the impingement structure.

대표청구항 ▼

We claim: 1. A gas turbine engine vane assembly comprising: an airfoil extending from a vane platform and adapted to extend through a main gas flow passage of said gas turbine engine; an impingement structure disposed adjacent said vane platform and defining at least first and second plenums thereb

We claim: 1. A gas turbine engine vane assembly comprising: an airfoil extending from a vane platform and adapted to extend through a main gas flow passage of said gas turbine engine; an impingement structure disposed adjacent said vane platform and defining at least first and second plenums therebetween, said first and second plenums being in fluid flow communication and defined in part by said vane platform, said vane platform having first and second surfaces respectively defined within said first and second plenums, said impingement structure having first impingement holes communicating between a source of secondary cooling air and said first plenum for impingement cooling of said first surface, and second impingement holes communicating between said first plenum and said second plenum for impingement cooling of said second surface, said second plenum being wholly disposed upstream of said first plenum relative to a primary gas flow direction through said main gas flow passage, said second plenum disposed downstream of said first plenum relative to secondary cooling air flow therethrough; and an exhaust passage communicating between said second plenum and said main gas flow passage for exhausting said secondary cooling air flow into said main gas flow passage. 2. The vane assembly as defined in claim 1, wherein said first and second plenums are axially aligned in said primary gas flow direction. 3. The vane assembly as defined in claim 2, wherein said first and second plenums are axially disposed on opposed sides of a dividing member extending between said vane platform and said impingement structure. 4. The vane assembly as defined in claim 2, wherein said impingement structure includes an impingement plate and a casing disposed radially outward therefrom. 5. The vane assembly as defined in claim 4, wherein at least said second impingement holes are defined in said impingement plate. 6. The vane assembly as defined in claim 4, wherein said first impingement holes are defined in said casing. 7. The vane assembly as defined in claim 1, wherein said first and second plenums communicate via a third plenum. 8. The vane assembly as defined in claim 7, wherein said third plenum is disposed radially outward from said first and second plenums. 9. The vane assembly as defined in claim 8, wherein said impingement structure includes an impingement plate and a casing disposed radially outward therefrom, and said third plenum is defined between said impingement plate and said casing. 10. The vane assembly as defined in claim 1, wherein said airfoil includes an internal cooling passage therein, said internal cooling passage being in fluid flow communication with said first plenum. 11. The vane assembly as defined in claim 1, wherein said exhaust passage exhausts said secondary cooling air into said main gas flow passage upstream of said airfoil. 12. The vane assembly as defined in claim 11, wherein said exhaust passage is defined in said vane platform. 13. A gas turbine engine vane assembly comprising: an airfoil extending from a vane platform; an impingement structure disposed adjacent said vane platform and cooperating therewith to define first and second plenums in serial fluid flow communication, said first and second plenums being axially adjacent one another in a primary gas flow direction and separated form one another by a dividing member radially extending between said outer vane platform and said impingement structure, the impingement structure including first means for communicating between a source of secondary cooling air and said first plenum and for impingement cooling of a portion of said vane platform defining said first plenum, the impingement structure including second means for communicating secondary cooling air between said first plenum and said second plenum and for impingement cooling of a portion of said vane platform defining said second plenum; and means for providing fluid flow communication between said second plenum and said main gas flow passage to exhaust said secondary cooling air into said main gas flow passage. 14. The vane assembly as defined in claim 13, wherein said second plenum is disposed upstream of said first plenum relative to said primary gas flow direction, and downstream of said first plenum relative to flow of said secondary cooling air through said impingement structure. 15. The vane assembly as defined in claim 13, wherein said impingement structure includes an impingement plate and an outer casing disposed radially outward therefrom. 16. The vane assembly as defined in claim 15, wherein said first and second plenums radially extend between said vane platform and an inner surface of said impingement plate. 17. The vane assembly as defined in claim 15, wherein said impingement plate abuts said dividing member. 18. The vane assembly as defined in claim 16, wherein at least said second means is defined in said impingement plate. 19. The vane assembly as defined in claim 15, wherein said first means is defined in said outer casing. 20. The vane assembly as defined in claim 13, wherein said exhaust passage exhausts said secondary cooling air into said main gas flow passage upstream of said airfoil. 21. The vane assembly as defined in claim 20, wherein said exhaust passage is defined in said vane outer platform. 22. The vane assembly as defined in claim 16, wherein said first and second plenums communicate via a third plenum. 23. The vane assembly as defined in claim 22, wherein said third plenum is disposed radially outward from said first and second plenums, between said impingement plate and said outer casing. 24. The vane assembly as defined in claim 13, wherein said airfoil includes an internal cooling passage therein, said internal cooling passage being in fluid flow communication with said first plenum. 25. A method of cooling a vane assembly in a gas turbine engine, the vane assembly having an airfoil extending from a vane platform and being adapted to extend through a main gas flow passage of the gas turbine engine, the method comprising: impinging secondary cooling air against a first portion of said vane platform adjacent a tailing edge of said airfoil; redirecting at least some of said secondary cooling air upstream relative to a direction of primary gas flow through said main gas flow passage, following said impingement cooling of said first portion; impinging said redirected secondary cooling air against a second portion of said vane platform adjacent a leading edge of said airfoil; and exhausting said secondary cooling air into said main gas flow passage upstream of said airfoil relative to said primary gas flow direction.