초록 ▼

A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is provided. The secondary flow tur

A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is provided. The secondary flow turbine cooling system provides uniform cooling air having a similar pressure and temperature in a recuperated gas turbine engine as the compressor discharge air of a non-recuperated gas turbine engine. A method for uniform cooling of high pressure turbine module components using the secondary flow turbine cooling air system is also provided.

대표청구항 ▼

We claim: 1. A method for cooling high pressure turbine module components of a recuperated turbine engine comprising the steps of: providing compressor discharge air by discharging cold compressed air from a compressor; providing secondary flow cooling air by diverting a portion of the compressor d

We claim: 1. A method for cooling high pressure turbine module components of a recuperated turbine engine comprising the steps of: providing compressor discharge air by discharging cold compressed air from a compressor; providing secondary flow cooling air by diverting a portion of the compressor discharge air through an open passage of a strut of a recuperator and turbine support adapter; flowing the secondary flow cooling air from the strut and along an inner flow separator; and cooling the high pressure turbine module components with the secondary flow cooling air. 2. The method of claim 1 wherein the recuperator and turbine support adapter comprises: an annular outer strutted body, the outer strutted body comprising a first outer ring and first inner ring, the first outer ring connected to the first inner ring by a plurality of outer struts, and at least one outer open passage through the first inner ring, the outer open passage being positioned between two of the outer struts; an annular inner strutted body, the inner strutted body comprising a second outer ring and a second inner ring, the second outer ring connected to the second inner ring by a plurality of inner struts, wherein at least one of the inner struts comprises the open passage wherein the open passage is an inner open passage, the inner open passage being aligned with the outer open passage; and a thermal spring connecting the first inner ring of the outer strutted body to the second outer ring of the inner strutted body; wherein the compressor discharge air flows through the outer open passage to the inner open passage of the inner strut and then to the inner flow separator. 3. The method of claim 2 wherein the second inner ring of the inner strutted body of the recuperator and turbine support adapter further comprises an aft flange, wherein the secondary flow cooling air flows forward of the aft flange to the inner flow separator. 4. The method of claim 1 wherein the turbine module components comprise a high pressure turbine shroud, a high pressure turbine nozzle, a high pressure turbine blade tip, a transition liner, or a turbine bearing support housing. 5. The method of claim 1 wherein the cooling of high pressure turbine module components is uniform. 6. A method for uniform cooling of high pressure turbine module components of a recuperated turbine engine comprising the steps of: providing compressor discharge air by discharging cold compressed air from a compressor, wherein the compressor discharge air flows through an outer flow path to a recuperator and turbine support adapter, the recuperator and turbine support adaptor comprising an annular outer strutted body, the outer strutted body comprising a first outer ring and first inner ring, the first outer ring connected to the first inner ring by a plurality of outer struts, and further comprising at least one outer open passage through the first inner ring, the outer open passage being positioned between two of the outer struts and an open slot at an aft end of the first inner ring of the outer strutted body, an annular inner strutted body, the inner strutted body comprising a second outer ring and a second inner ring, the second outer ring connected to the second inner ring by a plurality of inner struts, at least one of the inner struts further comprising an inner open passage wherein the inner open passage is aligned with the outer open passage, and a thermal spring connecting the first inner ring of the outer strutted body to the second outer ring of the inner strutted body; providing a secondary flow cooling air by diverting a portion of the cold compressed air through the outer open passage and the open slot to the inner open passage of the inner strut of the recuperator and turbine support adapter; flowing the secondary flow cooling air from the inner open passage of the inner struts along an inner flow separator; and cooling the high pressure turbine module components with the secondary flow cooling air. 7. The method of claim 6 wherein the compressor discharge air has a temperature of from about 500.degree. F. to about 700.degree. F. before it is diverted to the inner open passage of the inner strut. 8. The method of claim 6 wherein the secondary flow cooling air, after flowing from the open passage, has from about 90% to about 100% of the pressure of the compressor discharge air. 9. The method of claim 6 wherein the temperature of the secondary flow cooling air increases by only about 5.degree. F. to about 100.degree. F. after moving through the inner open passage of the inner struts. 10. The method of claim 6 wherein the temperature of the secondary flow cooling air increases by only about 50.degree. F. to about 75.degree. F. after moving through the inner open passage of the inner struts. 11. The method of claim 6 wherein the secondary flow cooling air has a minimum flow area of about 1 square inch when cooling the turbine module components. 12. The method of claim 6 wherein the secondary flow cooling air has a minimum flow area of about 2 square inches when cooling the turbine module components. 13. The method of claim 6 wherein the portion of compressor discharge air diverted is about 5%. 14. The method of claim 6 wherein the secondary flow cooling air, after flowing from the radial gap between the outer strutted body and the inner strutted body and the open passages of the struts, has from about 90% to about 100% of the pressure of the compressor discharge air.