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A turbine engine resonator comprising a panel and a vessel. The panel is along a flow path within the engine and has an aperture. The vessel has a mounting flange secured to the panel. The flange has an aperture mated to the aperture of the panel. The vessel has a body secured to the mounting flang

A turbine engine resonator comprising a panel and a vessel. The panel is along a flow path within the engine and has an aperture. The vessel has a mounting flange secured to the panel. The flange has an aperture mated to the aperture of the panel. The vessel has a body secured to the mounting flange with an interior of the body in communication with the flange aperture. A first portion of the panel extends into the mounting flange aperture and may redirect a leakage flow, if any, to limit an effect of leakage upon resonator performance.

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What is claimed is 1. A turbine engine resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange wit

What is claimed is 1. A turbine engine resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange with an interior of the body in communication with the flange aperture, wherein: a first portion of the panel extends into the mounting flange aperture. 2. The resonator of claim 1 wherein: a gap, open toward the body interior, circumscribes the first portion. 3. The resonator of claim 1 wherein: the first portion is an uninterrupted collar. 4. The resonator of claim 1 wherein: a gap, open toward the body interior, fully circumscribes the first portion. 5. The resonator of claim 4 wherein: the gap has a median thickness of 0.002-0.09 inch and a median length of at least 0.15 inch. 6. The resonator of claim 1 wherein: mating seats of the panel and flange, respectively circumscribing the panel aperture and flange aperture are compressively engaged in the absence of a gasket. 7. The resonator of claim 1 wherein: the resonator body comprises a neck and an enlarged main body inboard of the neck, the neck extending radially outboard from a forward end of the main body. 8. The resonator of claim 1 wherein: the resonator body comprises a neck and an enlarged main body inboard of the neck, main body having a convex first circumferential side and a concave second circumferential side converging inboard. 9. The resonator of claim 1 wherein: the resonator body comprises a pair of sheet metal stampings respectively forming a pair of circumferential sides and an inboard bracket mounting the body to a plurality of other resonators. 10. A turbine engine comprising: a circumferential array of resonators of claim 1 each said panel secured to a single said resonator vessel; and a circumferential array of augmentor vanes interspersed with said panels. 11. A turbine engine resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange with an interior of the body in communication with the flange aperture, wherein: at least one of the mounting flange and panel form means for directing a leakage flow so as to limit an effect of said leakage flow upon resonator performance. 12. The resonator of claim 11 wherein: the means comprises a lip depending from the panel only partially into the flange. 13. A method for engineering a turbine engine centerbody resonator, the resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange with an interior of the body in communication with the flange aperture, the method comprising: configuring a protrusion of a first portion of the panel into the mounting flange aperture to produce a leakage flow redirection effective to limit a leakage flow sensitivity of the resonator. 14. The method of claim 13 wherein configuring comprises: testing with a controlled leakage; and measuring a resonator performance at a plurality of conditions with the controlled leakage. 15. The method of claim 13 wherein configuring comprises: testing with a controlled leakage; and measuring a resonator performance at a across a plurality of frequency values for each of a plurality of ΔP/P values. 16. The method of claim 13 wherein configuring comprises: varying a length of protrusion of the first portion; and varying a thickness of a gap around the first portion. 17. A turbine engine resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange with an interior of the body in communication with the flange aperture, wherein: the panel has a seat circumscribing the panel aperture; the mounting flange has: a seat circumscribing the mounting flange aperture; and a pair of mounting ears secured to the panel by an associated fastener to hold the mounting flange seat engaged to the panel seat by an interference mounting. 18. The resonator of claim 17 wherein: in a relaxed state of the mounting flange, with the mounting flange seat contacting the panel seat, there is a gap between each of the pair of mounting ears and an associated mating portion of the panel. 19. The resonator of claim 17 wherein: a lip portion of the mounting flange extends into the mounting flange aperture. 20. A turbine engine resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange with an interior of the body in communication with the flange aperture, wherein: at least one of the mounting flange and panel form means for interference mounting the mounting flange to the panel. 21. The apparatus of claim 20 wherein: the resonator is a single port resonator; and the body has a single interior. 22. A method for engineering a turbine engine centerbody resonator, the resonator comprising: a panel along a flow path within the engine and having an aperture; a resonator vessel having: a mounting flange secured to the panel and having an aperture mated to the aperture of the panel; and a body secured to the mounting flange with an interior of the body in communication with the flange aperture, the method comprising: configuring at least one of the panel and mounting flange to provide an interference mounting of the mounting flange to the panel effective to provide a desired leakage control. 23. The method of claim 22 wherein: in a relaxed state of the mounting flange, with a mounting flange seat contacting a panel seat, there is a gap between each of the pair of mounting ears and an associated mating portion of the panel; and the configuring comprises selecting a size of said gaps. 24. A turbine engine comprising: a case; a centerbody within the case and separated from the case by a core flowpath; a circumferential array of augmentor vanes extending between the centerbody and case; and a circumferential array of resonators within the centerbody and each having a port open to the core flowpath, wherein: each said resonator comprises a resonator body having a neck and an enlarged main body inboard of the neck, main body having a convex first circumferential side and a concave second circumferential side converging inboard, each first circumferential side nested with the second adjacent side of a first adjacent one of the resonators and each second circumferential side nested with the first adjacent side of a second adjacent one of the resonators. 25. The turbine engine of claim 24 wherein: in each resonator the neck extends radially outboard from a forward end of the main body. 26. The turbine engine of claim 24 wherein: each resonator body comprises a pair of sheet metal stampings respectively forming a pair of circumferential sides and an inboard bracket; and a common mounting ring is secured to the inboard brackets to secure each resonator to the other resonators. 27. The turbine engine of claim 24 wherein: each said resonator has a single said port formed in a uniquely associated ID panel.