Compressor bleed auxiliary turbine
A gas turbine engine is provided having a compressor section, a combustion section, and a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines. The one or more compressors and the one or more turbines are each rotatable about a longitudinal centerline of the gas turbine engine. Additionally, a bleed air flowpath is provided extending between an inlet in airflow communication with the compressor section and an outlet. An auxiliary turbine is positioned in airflow communication with the bleed air flowpath for extracting energy from a flow of bleed air through the bleed air flowpath.
1. A gas turbine engine comprising:
a compressor section including one or more compressors;
a combustion section located downstream of the compressor section;
a turbine section located downstream of the combustion section and including one or more turbines;
a bleed air flowpath extending between an inlet and an outlet, the inlet in airflow communication with the compressor section for receiving a flow of bleed air from the compressor section;
an auxiliary turbine positioned in airflow communication with the bleed air flowpath between the inlet of the bleed air flowpath and the outlet of the bleed air flowpath for extracting energy from the flow of bleed air through the bleed air flowpath; and
one or more shafts mechanically coupling the compressor section and the turbine section, wherein the auxiliary turbine is mechanically coupled to at least one of the one or more shafts for adding power to the at least one of the one or more shafts; and
an auxiliary compressor in airflow communication with the bleed air flowpath and configured as a core driven auxiliary compressor, wherein the auxiliary turbine is mechanically coupled to the one or more shafts independently of the auxiliary compressor.
2. The gas turbine engine of claim 1 , further comprising
a structural member extending from the compressor section to the turbine section adding structural support to the gas turbine engine, the structural member defining the bleed air flowpath.
3. The gas turbine engine of claim 1 , further comprising
a valve positioned in the bleed air flowpath, wherein the valve is configured to vary an amount of bleed airflow allowed through the bleed air flowpath.
4. The gas turbine engine of claim 1 , further comprising
a heat exchanger in thermal communication with the bleed air flowpath at a location upstream of the auxiliary turbine for reducing a temperature of the flow of bleed air therethrough; and
a heat exchanger in thermal communication with the bleed air flowpath at a location downstream of the auxiliary turbine for increasing a temperature of the flow of bleed air therethrough.
5. The gas turbine engine of claim 1 , wherein the compressor section, the combustion section, and the turbine section are each enclosed within an outer casing, and wherein the bleed air flowpath and auxiliary turbine are also enclosed within the outer casing.
6. The gas turbine engine of claim 1 , wherein auxiliary turbine is configured as a tip turbine.
7. The gas turbine engine of claim 1 , wherein the outlet of the bleed air flowpath is in airflow communication with the turbine section of the gas turbine engine.
8. The gas turbine engine of claim 1 , wherein the outlet of the bleed air flowpath is in airflow communication with an aft frame member of the turbine section of the gas turbine engine.
9. The gas turbine engine of claim 1 , wherein the turbine section includes a high pressure turbine, a low pressure turbine, and a stage of airflow injection nozzles, and wherein the outlet of the bleed air flowpath is in airflow communication with the stage of airflow injection nozzles.
10. A gas turbine engine comprising:
a compressor section including one or more compressors;
a turbine section located downstream of the compressor section and including one or more turbines;
a bleed air flowpath extending between an inlet and an outlet, the inlet in airflow communication with the compressor section for receiving up to at least five percent of an airflow through the compressor section;
an auxiliary turbine positioned in airflow communication with the bleed air flowpath between the inlet of the bleed air flowpath and the outlet of the bleed air flowpath for extracting energy from a flow of bleed air through the bleed air flowpath; and
one or more shafts mechanically coupling the compressor section and the turbine section, wherein the auxiliary turbine is mechanically coupled to at least one of the one or more shafts for adding power to the at least one of the one or more shafts; and
an auxiliary compressor in airflow communication with the bleed air flowpath and configured as a core driven auxiliary compressor, wherein the auxiliary turbine is mechanically coupled to the one or more shafts independently of the auxiliary compressor.
11. The gas turbine engine of claim 10 , further comprising
a structural member extending from the compressor section to the turbine section for strengthening the gas turbine engine, the structural member defining the bleed air flowpath.
12. The gas turbine engine of claim 10 , further comprising
a valve positioned in the bleed air flowpath, wherein the valve is configured to vary an amount of bleed airflow allowed through the bleed air flowpath.
13. The gas turbine engine of claim 10 , further comprising
a heat exchanger in thermal communication with the bleed air flowpath.
14. The gas turbine engine of claim 10 , wherein the outlet of the bleed air flowpath is in airflow communication with the turbine section of the gas turbine engine.
15. The gas turbine engine of claim 10 , wherein the outlet of the bleed air flowpath is in airflow communication with an aft frame member of the turbine section of the gas turbine engine.