Clearance control device
AssigneeGeneral Electric Company
InventorsGert Johannes van der Merwe, Joel Francis Kirk
Life of this patent
Estimating the term…
Abstract
A clearance control system includes one or more clearance control devices that include features for controlling the clearances between rotating and stationary components of an engine. In one exemplary aspect, a clearance control device utilizes a fluid to pressurize an actuation chamber defined by a compliant member of the clearance control device. The pressurization of the actuation chamber causes the actuation chamber to expand in a direction that changes the clearance between the stationary and rotating components of the engine.
Claims20
A clearance control device for an engine, the clearance control device defining an axial direction, a radial direction, and a circumferential direction, the clearance control device comprising:
- a hanger portion;
- a shroud portion;
- and
- a compliant member mechanically coupling the hanger portion with the shroud portion and defining an actuation chamber for receiving a fluid;
- wherein the shroud portion is moveable along the radial direction in response to a pressure change within the actuation chamber, and
- wherein the hanger portion, the shroud portion, and the compliant member are formed of a monolithic piece.
A gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the gas turbine engine comprising:
- a compressor section, a combustion section, and a turbine section in serial flow relationship and together at least partially defining a core air flowpath, the combustion section defining a diffuser cavity and a combustion chamber, the diffuser cavity located upstream of the combustion chamber;
- a clearance control device, comprising:
- a hanger portion;
- a shroud portion;
- and
- a compliant member mechanically coupling the hanger portion with the shroud portion and defining an actuation chamber in fluid communication with the diffuser cavity, wherein the shroud portion is moveable along the radial direction in response to a pressure change within the actuation chamber, and
- wherein the hanger portion, the shroud portion, and the compliant member are formed of a monolithic piece.
A method for adjusting the blade tip clearances of a gas turbine engine, the gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, and the gas turbine engine comprising a plurality of blades rotatable about the axial direction and a clearance control device disposed about the circumferential direction and spaced apart from the blades along the radial direction, the clearance control device having a hanger portion, a shroud portion, and a compliant member mechanically coupling the hanger portion with the shroud portion, the compliant member defining an actuation chamber, the method comprising:
- operating the gas turbine engine;
- and
- pressurizing the actuation chamber of the compliant member such that the shroud portion is displaced along the radial direction, wherein the hanger portion, the shroud portion, and the compliant member are formed of a monolithic piece.
Dependencies are inferred from the claim text.