Dual-use air turbine system for a gas turbine engine
First Claim
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.
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Accused Products
Abstract
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.
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Citations
16 Claims
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1. A dual-use air turbine system for a gas turbine engine of an aircraft, the dual-use air turbine system comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A method of using a dual-use air turbine system for a gas turbine engine of an aircraft, the method comprising:
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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. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16)
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Specification