초록 ▼

The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a

The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.

대표청구항 ▼

1. A combustion system for use with a cooling flow, comprising: a head end;an aft end;a transition nozzle extending from the head end to the aft end;an impingement sleeve surrounding the transition nozzle and defining a first cavity in communication with the head end for a first portion of the cooli

1. A combustion system for use with a cooling flow, comprising: a head end;an aft end;a transition nozzle extending from the head end to the aft end;an impingement sleeve surrounding the transition nozzle and defining a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow, wherein the impingement sleeve comprises a splitter rail extending circumferentially between the transition nozzle and the impingement sleeve in a choked flow region of the transition nozzle, wherein the splitter rail divides and defines the first cavity and the second cavity as separate spaces, wherein the first portion of the cooling flow is provided to the head end through the first cavity and is used to charge a flow of combustion gases, wherein the second portion of the cooling flow is provided to the aft end through the second cavity and is used for film cooling, wherein the transition nozzle comprises an integrated liner, a transition piece, and a first stage nozzle vane; anda plurality of cooling holes positioned about the transition nozzle and in communication with the second portion of the cooling flow, wherein a main portion of the second portion of the cooling flow is directed to the aft end in the second cavity and a secondary portion of the second portion of the cooling flow is directed to the plurality of cooling holes along the second cavity for film cooling. 2. The combustion system of claim 1, wherein the transition nozzle comprises an outer sidewall with a plurality of outer sidewall film cooling holes thereon. 3. The combustion system of claim 1, wherein the transition nozzle comprises an inner sidewall with a plurality of inner sidewall film cooling holes thereon. 4. The combustion system of claim 1, wherein the transition nozzle comprises a pressure side with a plurality of pressure side film cooling holes thereon. 5. The combustion system of claim 1, wherein the transition nozzle comprises a suction side with a plurality of suction side film cooling holes thereon. 6. The combustion system of claim 1, wherein the transition nozzle comprises an outer sidewall with a plurality of outer sidewall aft cooling holes thereon. 7. The combustion system of claim 1, wherein the transition nozzle comprises an inner sidewall with a plurality of inner sidewall aft cooling holes thereon. 8. The combustion system of claim 1, wherein the transition nozzle comprises a trailing end with a plurality of trailing end cooling holes thereon. 9. The combustion system of claim 1, further comprising a plurality of fuel nozzles in communication with the first portion of the cooling flow. 10. The combustion system of claim 1, wherein the transition nozzle comprises a thermal barrier coating thereon. 11. The combustion system of claim 1, further comprising a combustor at the head end and a turbine at the aft end. 12. A transition nozzle combustion system for use with a cooling flow, comprising: a transition nozzle extending from a head end to an aft end;the transition nozzle comprising an integrated liner, transition piece, and first stage nozzle vane; andan impingement sleeve surrounding the transition nozzle;the impingement sleeve defining a first cavity about a circumference of the transition nozzle and in communication with the head end for directing a first portion of the cooling flow and a second cavity about the circumference of the transition nozzle in communication with the aft end for directing a second portion of the cooling flow, wherein the impingement sleeve comprises a splitter rail extending circumferentially between the transition nozzle and the impingement sleeve in a choked flow region of the transition nozzle, wherein the splitter rail divides and defines the first cavity and the second cavity as separate spaces, wherein the first portion of the cooling flow is provided to the head end through the first cavity and is used to charge a flow of combustion gases, wherein the second portion of the cooling flow is provided to the aft end through the second cavity and is used for film cooling, wherein a main portion of the second portion of the cooling flow is directed to the aft end in the second cavity and a secondary portion of the second portion of the cooling flow is directed to a plurality of cooling holes along the second cavity for film cooling. 13. The transition nozzle combustion system of claim 12, wherein the transition nozzle comprises an outer sidewall with a plurality of outer sidewall film cooling holes thereon and an inner sidewall with a plurality of inner sidewall film cooling holes thereon. 14. The transition nozzle combustion system of claim 12, wherein the transition nozzle comprises a pressure side with a plurality of pressure side film cooling holes thereon and a suction side with a plurality of suction side film cooling holes thereon. 15. The transition nozzle combustion system of claim 12, wherein the transition nozzle comprises a trailing end with a plurality of trailing end cooling holes thereon. 16. A transition nozzle combustion system for use with a cooling flow, comprising: a transition nozzle extending from a head end to an aft end wherein the transition nozzle comprises an integrated liner, a transition piece, and a first stage nozzle vane; andan impingement sleeve surrounding the transition nozzle;the impingement sleeve defining a first cavity in communication with the head end for directing a first portion of the cooling flow and a second cavity in communication with the aft end for directing a second portion of the cooling flow;wherein the impingement sleeve comprises a splitter rail extending circumferentially between the transition nozzle and the impingement sleeve in a choked flow region of the transition nozzle, wherein the splitter rail divides and defines the first cavity and the second cavity as separate spaces, wherein the first portion of the cooling flow is provided to the head end through the first cavity and is used to charge a flow of combustion gases, wherein the second portion of the cooling flow is provided to the aft end through the second cavity and is used for film cooling; andwherein the transition nozzle comprising a plurality of cooling holes thereon in communication with the second portion of the cooling flow, wherein a main portion of the second portion of the cooling flow is directed to the aft end in the second cavity and a secondary portion of the second portion of the cooling flow is directed to the plurality of cooling holes along the second cavity for film cooling.