Pre-heating aircraft engine in standby mode
AssigneeRtx Corporation
InventorsRyan A. Mitchell, Robert B. Fowler
Life of this patent
Estimating the term…
Abstract
A method of operation is provided during which a heating fluid is directed through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode. The aircraft engine includes a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath. The heating fluid is directed through a second passage into the exhaust section when the aircraft engine is in a second mode. The heating fluid is directed through the second passage bypasses the turbine section.
Claims19
A method of operation, comprising:
- directing a heating fluid through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode, the aircraft engine including a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section, and the flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath;
- and
- directing the heating fluid through a second passage into the exhaust section when the aircraft engine is in a second mode, wherein the heating fluid directed through the second passage bypasses the turbine section;
- wherein the heating fluid is received from an aircraft environmental control system.
A method of operation, comprising:
- providing an aircraft engine in a standby mode, the aircraft engine including a flowpath, a compressor section, a combustor section and a turbine section, and the flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
- and
- directing a heating fluid into the aircraft engine to heat a component within the combustor section while the aircraft engine is in the standby mode, wherein a turbine rotor within the turbine section is substantially stationary during the standby mode, and wherein the heating fluid is received from an environmental control system of an aircraft.
An aircraft system, comprising:
- an environmental control system;
- an aircraft engine including a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section, and the flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath;
- and
- a fluid circuit fluidly coupled with the environmental control system, the fluid circuit including a first passage, a second passage and a flow regulator, the first passage fluidly coupled with the core flowpath along the combustor section, the second passage fluidly coupled with the core flowpath along the exhaust section and bypassing the combustor section and the turbine section, and the flow regulator configured to
- direct at least some of a heating fluid, received from the environmental control system, through the first passage and into the combustor section to heat a component within the combustor section when the aircraft engine is in a first standby mode;
- and
- direct at least some of the heating fluid, received from the environmental control system, through the second passage and into the exhaust section when the aircraft engine is in a second mode.
Dependencies are inferred from the claim text.