초록 ▼

A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compressor and a first turbine section in fluid communication with the

A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compressor and a first turbine section in fluid communication with the combustor. The first turbine section includes a low pressure turbine that drives the first fan section. A second fan section is supported between the first fan section and the compressor and is driven by a second turbine section disposed between the second fan section and the compressor for driving the second fan section.

대표청구항 ▼

1. A turbine engine comprising: a first fan section including a plurality of fan blades rotatable about an axis;a compressor in fluid communication with the first fan section;a first turbine driving the first fan section and the compressor;a second fan section disposed axially between the first fan

1. A turbine engine comprising: a first fan section including a plurality of fan blades rotatable about an axis;a compressor in fluid communication with the first fan section;a first turbine driving the first fan section and the compressor;a second fan section disposed axially between the first fan section and the compressor;a second turbine disposed between the second fan section and the compressor, the second turbine driving the second fan;a core flow path including the second turbine and leading into the compressor, a first bypass stream defined radially outward of the core flow path and a second bypass stream defined radially outward of the core and first bypass streams;a first splitter dividing airflow into a first flow into the core flow path; and the first bypass stream and a second flow into the second bypass stream;a second splitter aft of the first splitter dividing airflow between the first bypass stream and the core flow path, wherein the second turbine is disposed aft of the second splitter and within the core flow path;a first variable guide vane disposed axially forward of the second fan section; anda second variable guide vane disposed between the second fan section and the second turbine for controlling airflow through the second turbine. 2. The turbine engine as recited in claim 1 wherein the second variable vane is movable between a first position for driving the second turbine at a first speed and a second position for driving the second turbine at a second speed slower than the first speed. 3. The turbine engine as recited in claim 1, wherein the first variable guide vane is movable between a first and second positions to direct air into the second fan section. 4. The turbine engine as recited in claim 1, wherein no shroud is disposed proximate the second turbine. 5. The turbine engine as recited in claim 1, wherein the second fan section directs airflow into the first bypass stream and the core flow path. 6. The turbine engine as recited in claim 1, wherein each of the first variable vane and the second variable vane include control rods that extend radially outward through the first and second bypass streams. 7. The turbine engine as recited in claim 1, wherein the second turbine and the second fan section are attached to rotate with each other and independent of other rotating components along the axis. 8. A turbine engine comprising: a first fan section including a plurality of axially spaced stages rotatable about an axis;a core engine including a compressor axially aft of the first fan section, a combustor receiving core flow from the compressor and a first turbine driven by gases generated in the combustor, wherein the first turbine drives the first fan section and the compressor;a core flow passage providing air to the compressor;a first bypass passage disposed about the core engine;a second bypass passage disposed about the first bypass;a second fan section disposed between the first fan section and the compressor, the second fan section driving flow into both the first bypass passage and the core flow passage;a first variable vane disposed axially forward of the second fan section for directing airflow into the second fan section;a second turbine section disposed between the second fan section and the compressor in the core flow passage, the second turbine section driving the second fan section and disposed aft of a splitter dividing flow between the first bypass passage and the core flow passage; anda second variable vane disposed axially forward of the second turbine for controlling airflow through the second turbine section. 9. The turbine engine as recited in claim 8, wherein the second variable vane is movable between a first position for driving the second turbine at a first speed and a second position for driving the second turbine at a second speed slower than the first speed. 10. The turbine engine as recited in claim 8, wherein the second fan section and second turbine section are fixed to rotate together independent of the compressor and first turbine section. 11. The turbine engine as recited in claim 10, including at least one bearing assembly supporting rotation of the second fan section and the second turbine section. 12. The turbine engine as recited in claim 8, wherein the first variable vane is adjustable to change flow division between the first bypass passage and the core flow passage. 13. The turbine engine as recited in claim 8, wherein no shroud is disposed proximate the second turbine section. 14. A method of operating a turbine engine comprising defining a core gas flow path through a core engine, where the core engine includes a first fan section, a high pressure compressor, a combustor in communication with the high pressure compressor and a first turbine driven by gas flow generated by the combustor; andadjusting a first variable vane forward of a second fan section and a second variable vane forward of a second turbine disposed forward of the compressor in the core gas flow path to drive the second fan section such that the second fan section drives airflow into both a first bypass passage and a core flow passage, wherein the second variable vane is disposed aft of a splitter dividing flow between the core gas flow path and a first bypass passage. 15. The method as recited in claim 14, including positioning at least one of the first variable vane and the second variable vane to provide a maximum level of de-supercharging of flow into the core gas flow path at a first flight condition and positioning at least one of the first variable vane and the second variable vane to provide a minimum level of de-supercharging of flow into the core gas flow path at a second flight condition.