Piston ring sealing for pneumatic actuator
AssigneeHamilton Sundstrand Corporation
InventorBruce R. Schroder
Life of this patent
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Abstract
A piston configuration is provided, the configuration including a piston having a ring seat and a piston ring disposed within the ring seat. The piston ring is configured to form a sealing surface between a surface of the piston ring and a surface of the ring seat. The sealing surface is formed when a first pressure on a first side of the piston ring is greater than a second pressure on a second side of the piston ring. At least one fluid channel is configured to increase a surface area on the piston ring that is subject to the second pressure.
Claims17
A piston configuration for use in an aircraft engine comprising:
- a piston having a ring seat, the piston operably connected to a high temperature pneumatic valve of the aircraft engine, the valve operable in response to the piston to regulate airflow to aircraft systems;
- a piston ring disposed within the ring seat and configured to form a sealing surface between a surface of the piston ring and a surface of the ring seat, the sealing surface formed when a first pressure on a first side of the piston ring is greater than a second pressure on a second side of the piston ring;
- and
- at least one fluid channel configured to increase a surface area on the piston ring that is subject to the second pressure,
- wherein the at least one fluid channel is a groove that extends radially along a surface of the ring seat.
A piston system for use in an aircraft engine comprising:
- a piston wall defining an interior chamber;
- a piston located within the piston wall and dividing the interior chamber into a first chamber and a second chamber, the first chamber having a first pressure and located on a first side of the piston and the second chamber having a second pressure located on a second side of the piston, the piston having a ring seat located adjacent to the piston wall and the first pressure being greater than the second pressure, the piston operably connected to a high temperature pneumatic valve of the aircraft engine, the valve operable in response to the piston to regulate airflow to aircraft systems;
- a piston ring disposed within the ring seat and configured to form a seal between the piston ring, the piston wall, and the ring seat;
- and
- at least one fluid channel configured to increase a surface area on the piston ring that is subject to the second pressure,
- wherein the at least one fluid channel is a groove that extends radially along a surface of the ring seat.
A method of making a piston configuration for use in an aircraft engine, the method comprising:
- forming a piston having a ring seat;
- forming at least one fluid channel in one of the ring seat and a piston ring;
- disposing the piston ring within the ring seat, and
- forming a sealing surface between a surface of the piston ring and a surface of the ring seat, the sealing surface formed when a first pressure on a first side of the piston ring is greater than a second pressure on a second side of the piston ring wherein the at least one fluid channel is configured to increase a surface area on the piston ring that is subject to the second pressure;
- and
- operably connecting the piston to a high temperature pneumatic valve of the aircraft engine, the valve operable in response to the piston to regulate airflow to aircraft systems,
- wherein the at least one fluid channel is formed as a groove that extends radially along a surface of the ring seat.
Dependencies are inferred from the claim text.