Clearance control device
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.
1. 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.
2. The clearance control device of claim 1 , wherein the compliant member is a bellow spring extending between the hanger portion and the shroud portion, and wherein the bellow spring undulates along the radial direction.
3. The clearance control device of claim 1 , wherein the hanger portion comprises:
a forward wall;
an aft wall; and
a top wall extending between the forward wall and the aft wall, the top wall defining a feed opening in fluid communication with the actuation chamber.
4. The clearance control device of claim 1 , wherein the hanger portion includes a forward wall having a front surface and an aft surface, the forward wall defining a plurality of openings therethrough, the aft surface at least partially defining a cooling plenum, and wherein the compliant member includes an inner wall and an outer wall defining a cooling passage therebetween, the cooling passage in fluid communication with the cooling plenum, and wherein the shroud portion further includes a shroud segment defining a cooling cavity, the cooling cavity in fluid communication with the cooling passage.
5. The clearance control device of claim 4 , wherein the shroud segment includes an inner wall having an inner surface and an outer surface opposite the inner surface, the inner wall partially at least partially defining the cooling cavity, and wherein the inner wall defines a plurality of cooling holes extending therethrough, at least one of the cooling holes includes an outer opening defined by the outer surface of the inner wall and an inner opening defined by the inner surface of the inner wall, and wherein the inner opening is spaced apart from the outer opening along the axial direction.
6. The clearance control device of claim 1 , wherein the clearance control device further comprises:
an axial ligament mechanically coupling the shroud portion with the hanger portion, the axial ligament having an axial member extending along the axial direction.
7. The clearance control device of claim 1 , wherein the clearance control device extends between a forward end and an aft end along the axial direction, between a first end and a second end along the circumferential direction, and between a top end and a bottom end along the radial direction, the clearance control device further defining a radial centerline, and wherein the compliant member is a first compliant member, and wherein the clearance control device further comprises:
a second compliant member, and
wherein the shroud portion comprises:
a first shroud segment positioned between the first end and the radial centerline; and
a second shroud segment positioned between the second end and the radial centerline;
wherein the first compliant member mechanically couples the first shroud segment with the hanger portion and the second compliant member mechanically couples the second shroud segment with the hanger portion.
8. The clearance control device of claim 7 , wherein the actuation chamber is a first actuation chamber defined by the first compliant member and the second compliant member defines a second actuation chamber, and wherein the hanger portion further comprises:
a jumper cap defining a transition passage, the transition passage providing fluid communication between the first actuation chamber and the second actuation chamber.
9. The clearance control device of claim 7 , wherein the actuation chamber is a first actuation chamber defined by the first compliant member and the second compliant member defines a second actuation chamber, and wherein the hanger portion further comprises:
a forward wall;
an aft wall;
a top wall extending between the forward wall and the aft wall; and
a mid-span support extending in a plane along the axial and the radial directions and having a thickness in the circumferential direction, the mid-span support extending from the top wall and the forward wall of the hanger portion and positioned between the first compliant member and the second compliant member.
10. The clearance control device of claim 1 , wherein the shroud portion comprises a first shroud segment, the first shroud segment extending between a first end and a second end along the circumferential direction, and wherein the compliant member is a bellow spring extending between the hanger portion and the shroud portion, the bellow spring comprising:
a forward portion;
an aft portion spaced apart from the forward portion along the axial direction;
a first portion connecting the forward portion with the aft portion proximate the first end of the first shroud segment; and
a second portion connecting the forward portion with the aft portion proximate the second end of the first shroud segment;
wherein the forward portion, the aft portion, the first portion, and the second portion of the bellow spring undulate along the radial direction.
11. The clearance control device of claim 10 , wherein the forward and aft portions oscillate along the axial direction as the forward and aft portions undulate along the radial direction and wherein the first and second portions oscillate along the circumferential direction as the first and second portions undulate along the radial direction.
12. The clearance control device of claim 10 , wherein the forward portion, the aft portion, the first portion, and the second portion of the bellow spring each include an inner wall and an outer wall defining a cooling passage therebetween, and wherein the cooling passage defined by the forward portion and the cooling passage defined by the aft portion are in fluid communication via a bridge passageway extending along the axial direction and defined by a bridge.
13. The clearance control device of claim 10 , wherein the actuation chamber is a deadheaded chamber.
14. The clearance control device of claim 10 , wherein the shroud portion comprises a shroud segment defining a bleed passageway in fluid communication with the actuation chamber, the bleed passageway configured to selectively allow the fluid within the actuation chamber to bleed out.
15. 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.
16. The gas turbine engine of claim 15 , wherein the hanger portion defines a feed opening that provides fluid communication between the actuation chamber and the diffuser cavity, and wherein the gas turbine engine further comprises:
a control valve in fluid communication with the feed opening for selectively allowing an amount of fluid into the actuation chamber of the clearance control device.
17. The gas turbine engine of claim 15 , wherein the compliant member is a bellow spring extending between the hanger portion and the shroud portion along the radial direction, and wherein the bellow spring undulates along the radial direction.
18. The gas turbine engine of claim 15 , wherein the clearance control device extends between a forward end and an aft end along the axial direction, between a first end and a second end along the circumferential direction, and between a top end and a bottom end along the radial direction, the clearance control device further defining a radial centerline, and wherein the compliant member comprises a first compliant member and a second compliant member, and wherein the shroud portion comprises:
a first shroud segment positioned toward the first end with respect to the radial centerline; and
a second shroud segment positioned toward the second end with respect to the radial centerline;
wherein the first and second shroud segments each extend between a first end and a second end along the circumferential direction and each have a first sidewall at the first end and a second sidewall at the second end, the first sidewall of each of the shroud segments defining a first slit portion and the second sidewall of each of the shroud segments defining a second slit portion, the second slit portion of the first shroud segment and the first slit portion of the second shroud segment forming a slit, and wherein the clearance control device further comprises:
a spline seal positioned within the slit for sealing the first shroud segment and the second shroud segment along the radial direction during operation of the gas turbine engine.
19. 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.
20. The gas turbine engine of claim 15 , wherein the hanger portion includes a forward wall having a front surface and an aft surface, the forward wall defining a plurality of openings therethrough, the aft surface at least partially defining a cooling plenum, and wherein the compliant member includes an inner wall and an outer wall defining a cooling passage therebetween, the cooling passage in fluid communication with the cooling plenum, and wherein the shroud portion further includes a shroud segment defining a cooling cavity, the cooling cavity in fluid communication with the cooling passage.