Turbine vane assembly for controlling tip clearance
AssigneePratt & Whitney Canada Corp.
InventorsGuy Lefebvre, Remy Synnott, Rabih Kamal Kassab
Life of this patent
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Abstract
An aircraft engine having a turbine assembly including a bearing housing having a central axis, a first-stage vane ring and a second-stage vane ring. The first-stage vane ring is positioned in concentric relation with the bearing housing via a first circumferential array of lugs and slots between the bearing housing and the first-stage vane ring. The second-stage vane ring is positioned in concentric relation to the first-stage vane ring via a second circumferential array of lugs and slots between the first-stage vane ring and the second-stage vane ring.
Claims15
A turbine assembly for an aircraft engine, comprising:
- a bearing housing having a central axis;
- a first-stage vane ring positioned in concentric relation with the bearing housing via a first circumferential array of lugs and slots between the bearing housing and the first-stage vane ring;
- and
- a second-stage vane ring positioned in concentric relation to the first-stage vane ring via a second circumferential array of lugs and slots between the first-stage vane ring and the second-stage vane ring.
An aircraft engine comprising:
- a turbine including a first-stage vane ring, a turbine rotor and a second-stage vane ring disposed in series along a central axis, the turbine rotor having a row of turbine blades surrounded by an inner surface of an outer shroud of the second-stage vane ring, the turbine blades having tips spaced from the inner surface of the outer shroud by a tip clearance gap;
- and
- a bearing supporting the turbine rotor for rotation about the central axis;
- wherein a first circumferential array of lugs and slots centralizes the first-stage vane ring on a bearing housing of the bearing, and wherein a second circumferential array of lugs and slots centralizes the second-stage vane ring on the first-stage vane ring.
Dependencies are inferred from the claim text.