Single stage engine bleed
AssigneeHamilton Sundstrand Corporation
InventorMichael Ronan
Life of this patent
Estimating the term…
Abstract
An environmental control system is provided. The environmental control system may receive pressurized air from a single supply line. A pressure regulating turbomachine may be located within the supply line. A motor-generator may be coupled to the pressure regulating turbomachine. In response to a pressure in the supply line being less than a desired pressure in the environmental control system, the motor-generator may supply energy to the pressure regulating turbomachine, causing the pressure regulating turbomachine to function as a compressor. In response to a pressure in the supply line being greater than a desired pressure in the environmental control system, the pressure regulating turbomachine may function as a turbine and supply energy to the motor-generator.
Claims18
An environmental control system comprising:
- a pressure regulating turbomachine located within a supply line, wherein a location of the supply line is selected such that a minimum pressure in the supply line is less than a desired pressure in the environmental control system, and wherein a maximum pressure in the supply line is greater than the desired pressure in the environmental control system;
- and
- a motor-generator coupled to the pressure regulating turbomachine,
- wherein the pressure regulating turbomachine is configured to supply energy to the motor-generator, and
- wherein the motor-generator is configured to supply energy to the pressure regulating turbomachine.
An aircraft environmental control system comprising:
- a gas turbine engine including a compressor and a primary generator;
- a supply line coupled to the compressor, wherein a pressure in the supply line is less than a desired pressure in the aircraft environmental control system during idle, and wherein the pressure in the supply line is greater than the desired pressure in the aircraft environmental control system during cruise;
- a pressure regulating turbomachine located within the supply line;
- and
- a motor-generator coupled to the pressure regulating turbomachine and the primary generator.
An aircraft power distribution system comprising:
- a primary aircraft power distribution system comprising a primary generator coupled to an engine gearbox;
- and
- a secondary aircraft power distribution system comprising:
- a pressure regulating turbomachine located within a supply line, wherein a pressure in the supply line is less than a desired pressure in an environmental control system during idle, and wherein the pressure in the supply line is greater than the desired pressure in the environmental control system during cruise;
- and
- a motor-generator coupled to the pressure regulating turbomachine,
- wherein the motor-generator is configured to produce power that is supplied to the primary aircraft power distribution system through the secondary aircraft power distribution system, and
- wherein the motor-generator is configured to supply power from the primary aircraft power distribution system to the pressure regulating turbomachine.
Dependencies are inferred from the claim text.