Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations
View Patent ↗A gas turbine combustor ( 10 ) comprises a main swirler assembly ( 400 ) comprising an annulus casting ( 410 ) itself comprising a modified downstream end ( 418 ) fitted into an reversed-edge base plate ( 450 ) that comprises an opening ( 453 ) defined by a lip ( 452 ) oriented upstream. The lip ( 452 ) comprises an upstream surface ( 457 ), an outboard surface ( 458 ) and an inboard surface ( 459 ). In certain embodiments the modified downstream end ( 418 ) has a shape to fit against the upstream surface ( 457 ) and the outboard surface ( 458 ) so as to increase the natural frequency of the main swirler assembly ( 400 ) to above the natural frequency of the combustion in the gas turbine combustor ( 10 ).
1. A gas turbine can-annular combustor comprising:
a. a main swirler assembly comprising an annulus casting having an upstream end and a downstream end, and
b. a reversed-edged base plate comprising at least one opening defined peripherally by an upstream-oriented lip comprising an upstream surface, an outboard surface and an inboard surface;
the annulus casting downstream end contoured to engage the upstream-oriented lip.
2. The combustor of claim 1 , providing a fit between the downstream end and the lip effective to increase a natural frequency of the main swirler assembly during gas turbine operation beyond combustion acoustics natural frequencies.
3. The combustor of claim 2 , the fit being a tight fit having a tolerance between about 0 and 0.003 inch.
4. The combustor of claim 1 , the annulus casting downstream end contoured to engage the lip along the upstream surface and at least a portion of the outboard surface of the lip.
5. The combustor of claim 4 , a fit between the downstream end and the lip effective to elevate the natural frequency of the main swirler assembly above 700 cycles per second.
6. The combustor of claim 1 , the annulus casting downstream end contoured to engage the lip along the upstream surface and at least a portion of the inboard surface of the lip.
7. The combustor of claim 6 , a fit between the downstream end and the lip effective to elevate the natural frequency of the main swirler assembly above 700 cycles per second.
8. The combustor of claim 3 , the fit additionally effective to reduce or eliminate resonance-based cracking of the main swirler assembly.
9. The combustor of claim 8 , the annulus casting downstream end additionally comprising a diameter enlarged relative to an annulus casting downstream end corresponding to a conventional base plate, the enlarged diameter effective to reduce or eliminate flashback during operation.
10. The combustor of claim 5 , wherein the transmissibility of vibration through the main swirler assembly remains below about 10.
11. The combustor of claim 7 , wherein the transmissibility of vibration through the main swirler assembly remains below about 10.
12. The combustor of claim 1 , wherein a plurality of main swirler assemblies are arranged in the combustor, each comprising a respective annulus casting having an upstream end and a downstream end, each downstream end of each respective annulus casting contoured to engage a respective one of a plurality of upstream-oriented lips of the reversed-edged base plate providing a fit effective to increase a natural frequency of the respective main swirler assembly during gas turbine operation beyond combustion acoustics natural frequencies.
13. A main swirler assembly/base plate combination for a gas turbine combustor, comprising:
a. a main swirler assembly comprising an annulus casting having an upstream end and a downstream end, and
b. a reversed-edged base plate comprising an opening defined peripherally by an upstream-oriented lip comprising an upstream surface, an outboard surface and an inboard surface;
wherein the annulus casting downstream end is contoured to engage the upstream-oriented lip of the opening.
14. The combination of claim 13 , providing a fit between the downstream end and the lip effective to increase a natural frequency of the main swirler assembly during gas turbine combustor operation beyond combustion acoustics natural frequencies.
15. The combination of claim 14 , the fit additionally effective to enhance vibration damping compared to fit between a conventional base plate and a corresponding main swirler assembly.
16. The combination of claim 14 , the fit being a tight fit having a tolerance between about 0 and 0.003 inch.
17. The combination of claim 13 , the annulus casting downstream end contoured to engage the lip along the upstream surface and at least a portion of the outboard surface of the lip.
18. The combination of claim 13 , the annulus casting downstream end contoured to engage the lip along the upstream surface and at least a portion of the inboard surface of the lip.