Compressor casing with passive tip clearance control and endwall ovalization control
First Claim
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1. A gas turbine engine apparatus, comprising:
- a mechanical housing;
a first rotor with a plurality of first blades located within said mechanical housing and rotatable about a centerline, each of said plurality of first blades including a first tip;
a control ring located within and spaced from said mechanical housing;
a plurality of locating members fixedly coupled with said mechanical housing and slidably coupled with said control ring, said plurality of locating members positioning said control ring relative to said mechanical housing;
a non-rotatable ring with a plurality of vanes located within said mechanical housing and axially spaced from said first rotor, wherein said non-rotatable ring includes a tip shroud portion spaced from said first tips of said plurality of first blades, and wherein said non-rotatable ring is fixedly coupled with said control ring and moveable therewith; and
wherein relative motion may occur between said control ring and at least one of said plurality of locating members.
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Abstract
A passive clearance control system for a gas turbine engine component. The system provides a blade shroud that is isolated from the component case and can move radially to maintain blade clearance. A plurality of vane sectors define a stator ring including a blade shroud. The stator ring and the control ring are coupled together and mounted within the component by a plurality of radial extending mounting members.
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Citations
22 Claims
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1. A gas turbine engine apparatus, comprising:
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a mechanical housing;
a first rotor with a plurality of first blades located within said mechanical housing and rotatable about a centerline, each of said plurality of first blades including a first tip;
a control ring located within and spaced from said mechanical housing;
a plurality of locating members fixedly coupled with said mechanical housing and slidably coupled with said control ring, said plurality of locating members positioning said control ring relative to said mechanical housing;
a non-rotatable ring with a plurality of vanes located within said mechanical housing and axially spaced from said first rotor, wherein said non-rotatable ring includes a tip shroud portion spaced from said first tips of said plurality of first blades, and wherein said non-rotatable ring is fixedly coupled with said control ring and moveable therewith; and
wherein relative motion may occur between said control ring and at least one of said plurality of locating members. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A gas turbine engine apparatus, comprising:
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a case;
a rotatable first rotor with a plurality of circumferentially spaced first blades located within said case and about a centerline, each of said plurality of first blades including a first tip;
a control ring located within and spaced radially from said case;
a plurality of radial mounting members fixedly connected with said case, each of said plurality of radial mounting members extending radially and slidably engaging an opening in said control ring, wherein said plurality of locating members positioning said control ring relative to case; and
a plurality of vane sectors mounted in a substantially adjacent relationship within said case to form a non-rotatable ring axially spaced from said first rotor, each of said plurality of vane sectors includes an inner endwall and an outer endwall with at least one vane located between said endwalls, wherein each of said outer endwalls has an extension member extending therefrom including a shroud portion and a coupling portion, wherein each of said shroud portions extending along and spaced radially from said first tips and each of said coupling portions fixedly coupled with said control ring, and said plurality of vane sectors and said control ring are moveable together, and wherein relative radial motion may occur between at least one of said radial mounting members and said control ring. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19)
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20. A compressor passive clearance control system, comprising:
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a compressor case having a flowpath for working fluid flow;
a rotatable first rotor with a plurality of circumferentially spaced first blades located within said case and about a centerline, each of said plurality of first blades is disposed within said flowpath and includes a first tip;
a rotatable second rotor with a plurality of circumferentially spaced second blades located within said case and about said centerline, each of said plurality of second blades is disposed within said flowpath and includes a second tip;
a control ring located within said case;
a plurality of radial mounting members fixedly connected with said case, each of said plurality of radial mounting members extending radially and slidably engaging an opening in said control ring, wherein said plurality of locating members positioning said control ring relative to case; and
a plurality of vane sectors mounted in a substantially adjacent relationship within said case to form a non-rotatable ring axially spaced from said first rotor, each of said plurality of vane sectors includes an inner endwall and an outer endwall with at least one vane located between said endwalls and within said flowpath, wherein each of said outer endwalls has a fore extension member and an aft extension member, said fore extension member extending from said outer endwall and including a fore shroud portion and a fore coupling portion, wherein each of said fore shroud portions extending along and spaced radially from said first tips and each of said fore coupling portions fixedly coupled with a first portion of said control ring, and wherein said aft extension member extending from said outer endwall and including an aft shroud portion and an aft coupling portion, wherein each of said aft shroud portions extending along and spaced radially from said second tips and each of said aft coupling portions fixedly coupled with a second portion of said control ring, and said plurality of vane sectors and said control ring arc moveable together, a working fluid bleed to direct a portion of working fluid from said flowpath across said control ring; and
wherein relative radial motion may occur between at least one of said radial mounting members and said control ring. - View Dependent Claims (21, 22)
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Specification