Dual-use air turbine system for a gas turbine engine
A dual-use air turbine system for a gas turbine engine of an aircraft is provided. The dual-use air turbine system includes a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set. The dual-use air turbine system also includes a plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation. The valves are further operable to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation.
1. A dual-use air turbine system for a gas turbine engine of an aircraft, the dual-use air turbine system comprising:
a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set;
a plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation, wherein the valves comprise a first check valve, a high pressure shutoff valve, a main valve located upstream of the inlet of the variable area air turbine, a starter air valve located downstream of an outlet of the variable area air turbine, and a second check valve located between the outlet of the variable area air turbine and the main valve; and
a controller configured to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation of an environmental control system that provides conditioned air to a cabin of the aircraft, wherein the engine bleed air flow is provided from a lower pressure tap of the compressor section by the first check valve to the main valve and to the inlet of the variable area air turbine or the engine bleed air flow is provided from a higher pressure tap of the compressor section by the high pressure shut-off valve to the main valve and the inlet of the variable area air turbine.
2. The dual-use air turbine system as in claim 1 , wherein the controller is further configured to open the first check valve during a high power condition of the gas turbine engine and open the high pressure shut-off valve during an engine idle condition of the gas turbine engine.
3. The dual-use air turbine system as in claim 1 , wherein the controller is configured to open the main valve and the starter air valve during the engine start mode of operation to establish a flow path from aircraft ducting through the main valve, the variable area air turbine, the starter air valve, and an exhaust port.
4. The dual-use air turbine system as in claim 1 , wherein the controller is configured to open the starter air valve during an environmental control system off mode of operation to establish a flow path for the engine bleed air flow through the variable area air turbine, the starter air valve, and an exhaust port.
5. The dual-use air turbine system as in claim 1 , wherein the controller is configured to open the main valve during the environmental control system active mode of operation at a minimum pressure engine idle condition to establish a flow path for the engine bleed air flow through the main valve to aircraft ducting.
6. The dual-use air turbine system as in claim 1 , wherein the controller is configured to close the main valve and open the second check valve during the environmental control system active mode of operation at an engine off idle condition and at a high power condition to establish a flow path for the engine bleed air flow through the variable area air turbine and the second check valve to aircraft ducting.
7. The dual-use air turbine system as in claim 1 , wherein the controller is configured to open the main valve and open the second check valve during the environmental control system active mode of operation with a wing anti-ice air flow on to establish a flow path for the engine bleed air flow to aircraft ducting through the variable area air turbine and the main valve to provide heated air to a wing of the aircraft.
8. The dual-use air turbine system as in claim 1 , further comprising a clutch to selectively engage the variable area air turbine to drive rotation of the spool.
9. A method of using a dual-use air turbine system for a gas turbine engine of an aircraft, the method comprising:
controlling a plurality of valves in pneumatic ducting to direct an engine start air flow through an inlet of a variable area air turbine and drive rotation of a spool of the gas turbine engine during an engine start mode of operation, wherein the valves comprise a first check valve, a high pressure shutoff valve, a main valve located upstream of the inlet of the variable area air turbine, a starter air valve located downstream of an outlet of the variable area air turbine, and a second check valve located between the outlet of the variable area air turbine and the main valve; and
directing an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine to drive rotation of the spool during an environmental control system active mode of operation of an environmental control system that provides conditioned air to a cabin of the aircraft, wherein the engine bleed air flow is provided from a lower pressure tap of the compressor section by the first check valve to the main valve and to the inlet of the variable area air turbine or the engine bleed air flow is provided from a higher pressure tap of the compressor section by the high pressure shut-off valve to the main valve and the inlet of the variable area air turbine, wherein the variable area air turbine is mechanically linked to the spool of the gas turbine engine through a multi-speed gear set.
10. The method as in claim 9 , further comprising:
opening the first check valve during a high power condition of the gas turbine engine; and
opening the high pressure shut-off valve during an engine idle condition of the gas turbine engine.
11. The method as in claim 9 , further comprising:
opening the main valve and the starter air valve during the engine start mode of operation to establish a flow path from aircraft ducting through the main valve, the variable area air turbine, the starter air valve, and an exhaust port.
12. The method as in claim 9 , further comprising:
opening the starter air valve during an environmental control system off mode of operation to establish a flow path for the engine bleed air flow through the variable area air turbine, the starter air valve, and an exhaust port.
13. The method as in claim 9 , further comprising:
opening the main valve during the environmental control system active mode of operation at a minimum pressure engine idle condition to establish a flow path for the engine bleed air flow through the main valve to aircraft ducting.
14. The method as in claim 9 , further comprising:
closing the main valve and opening the second check valve during the environmental control system active mode of operation at an engine off idle condition and at a high power condition to establish a flow path for the engine bleed air flow through the variable area air turbine and the second check valve to aircraft ducting.
15. The method as in claim 9 , further comprising:
opening the main valve and opening the second check valve during the environmental control system active mode of operation with a wing anti-ice air flow on to establish a flow path for the engine bleed air flow to aircraft ducting through the variable area air turbine and the main valve to provide heated air to a wing of the aircraft.
16. The method as in claim 9 , further comprising selectively engaging the variable area air turbine to drive rotation of the spool.