Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines

A secondary flow turbine cooling air system for cooling recuperated turbine engine module components comprising:

• an outer flow path for compressor discharge air;
• a recuperator and turbine support adapter comprising:
• an annular outer strutted body, the outer strutted body comprising a first outer ring and a 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,
• 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 comprising an inner open passage running the length of the inner strut, wherein the inner open passage is aligned with the outer open passage, and wherein the recuperator and turbine support adapter is in fluid communication with the outer flow path through the inner strut, and
• a thermal spring connecting the first inner ring of the outer strutted body to the second outer ring of the inner strutted body;
• and
• an inner flow separator in fluid communication with the recuperator and turbine support adapter.

A secondary flow turbine cooling air system for cooling recuperated turbine engine module components comprising:

• an outer flow path for compressor discharge air;
• a recuperator and turbine support adapter comprising:
• an annular outer strutted body, the outer strutted body comprising a first outer ring and a 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, at least one of the inner struts comprising an inner open passage running the length of the inner strut wherein the inner open passage is aligned with the outer open passage, the inner open passage comprising a tube and a compliant duct, and wherein the recuperator and turbine support adapter is in fluid communication with the outer flow path through the inner strut, and
• a thermal spring connecting the first inner ring of the outer strutted body to the second outer ring of the inner strutted body;
• and
• an inner flow separator in fluid communication with the recuperator and turbine support adapter.

A secondary flow turbine cooling air system for cooling recuperated turbine engine module components comprising:

• an outer flow path for compressor discharge air;
• a recuperator and turbine support adapter comprising:
• an annular outer strutted body, the outer strutted body comprising a first outer ring and a 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, at least one of the inner struts comprising an inner open passage running the length of the inner strut the inner open passage being aligned with the outer open passage, wherein the inner open passage is pressurized and wherein the recuperator and turbine support adapter is in fluid communication with the outer flow path through the inner strut, and
• a thermal spring connecting the first inner ring of the outer strutted body to the second outer ring of the inner strutted body;
• and
• an inner flow separator in fluid communication with the recuperator and turbine support adapter.

A recuperated turbine engine comprising:

• a compressor;
• an outer flow path for passage of compressor discharge air discharged from the compressor;
• a recuperator and turbine support adapter comprising an annular outer strutted body, the outer strutted body comprising a first outer ring and a first inner ring, the first outer ring connected to 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, at least one of the inner struts further comprising an inner open passage running the length of the inner strut wherein the inner open passage is aligned with the outer open passage, wherein the recuperator and turbine support adapter is in fluid communication with the outer flow path through the outer open passage to the inner open passage of the inner strut and a thermal spring connecting the first inner ring of the outer strutted body to the second outer ring of the inner strutted body;
• an inner flow guide in fluid communication with the recuperator and turbine support adapter;
• and
• turbine module components in fluid communication with the inner flow guide.

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.

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.