Author
Steven Hillier
Bio: Steven Hillier is an academic researcher from Rolls-Royce Holdings. The author has contributed to research in topics: Shroud & Ceramic. The author has an hindex of 7, co-authored 19 publications receiving 223 citations.
Topics: Shroud, Ceramic, Turbine, Ceramic matrix composite, Track (disk drive)
Papers
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Patent•
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TL;DR: In this article, the authors describe a hollow section that defines an inlet (44) and an outlet (64, 66) for the passage of coolant through a turbine rotor.
Abstract: A ceramic seal segment (30) for a shroud ring (21) of a rotor (15) of a gas turbine engine (10), the ceramic seal segment (30) positioned radially adjacent the rotor (15) and characterised by being a hollow section that defines an inlet (44) and an outlet (64, 66) for the passage of coolant therethrough.
100 citations
Patent•
04 Mar 2014TL;DR: In this article, a gas turbine engine is formed from a continuous fiber reinforced ceramic matrix composite (CMC), which has a sealing portion which makes sealing contact with an adjacent component of the engine.
Abstract: A component (31) of a gas turbine engine is formed from a continuous fibre reinforced ceramic matrix composite (CMC). The component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine. The sealing portion comprises a recess (35) formed in the CMC and filled with a finer grade ceramic (36) relative to the surrounding CMC, a metal or an intermetallic.
22 citations
Patent•
25 Mar 2014TL;DR: In this paper, a seal segment is provided for a shroud ring of a rotor of a gas turbine engine, which is positioned, in use, radially adjacent the rotor, and two or more spaced passageways can be contained within each passageway.
Abstract: A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment has two or more spaced passageways. In use, a respective support bar can be contained within each passageway. The support bars allow attachment of the seal segment to the engine casing. Each passageway has an elliptical or substantially elliptical cross-section with a minor diameter and a major diameter, the minor diameter being substantially aligned with the radial direction. The respective support bar has a correspondingly elliptical or substantially elliptical cross-section for a close fit in the passageway.
16 citations
Patent•
31 Oct 2013TL;DR: In this paper, a method of forming a ceramic matrix composite gas turbine engine component includes the steps of: providing a plurality of green sub-elements of the component, each sub-element containing stacked plys of continuous fibre reinforcement embedded in a green ceramic matrix; assembling the subelements into an arrangement in which each subelement contacts at least one other subelement, the arrangement corresponding in shape to the final component.
Abstract: A method of forming a ceramic matrix composite gas turbine engine component includes the steps of: providing a plurality of green sub-elements of the component, each sub-element containing stacked plys of continuous fibre reinforcement embedded in a green ceramic matrix; assembling the sub-elements into an arrangement in which each sub-element contacts at least one other sub-element, the arrangement corresponding in shape to the final component; and sintering the assembled sub-elements to fuse the ceramic matrix within each sub-element and between contacting sub-elements, thereby forming the component as a ceramic matrix composite unitary body. An alternative method includes ceramic cement being provided at the contact interfaces between the sub-elements and the assembled sub-elements to fuse the ceramic cement, thereby forming the component as a ceramic matrix composite unitary body.
15 citations
Patent•
24 Nov 2015TL;DR: In this paper, a turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments, and an impingement tube is used to direct cooling air onto the blade track segments.
Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
14 citations
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27 Jan 2011TL;DR: In this article, an annular support member (14), a turbine shroud (12), and a spring (32) are arranged between the support member and the turbine shroud to push the shroud to a concentric position within the support members.
Abstract: A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).
108 citations
Patent•
15 Sep 2011TL;DR: A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment; and a hanger received in the open channel of each shrouded segment and mechanically coupled to the stationary structure, each hanger passing through the respective open channel, the enlarged
Abstract: A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure.
63 citations
Patent•
22 Feb 2012TL;DR: In this paper, a gas turbine engine shroud is constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface.
Abstract: A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.
57 citations
Patent•
01 Dec 2011TL;DR: In this article, an annular flowpath was provided for a gas turbine engine having a centerline axis. The flowpath member had a flowpath surface and an opposed back surface, and had a cross-sectional shape comprising a generally cylindrical forward section and an aft section that extended aft and radially outward at a non-perpendicular, non-parallel angle to the centerline.
Abstract: A turbine flowpath apparatus is provided for a gas turbine engine having a centerline axis. The apparatus includes: an annular flowpath member of low-ductility material, the flowpath member having a flowpath surface and an opposed back surface, and having a cross-sectional shape comprising a generally cylindrical forward section and an aft section that extends aft and radially outward at a non-perpendicular, non-parallel angle to the centerline axis; an annular stationary structure surrounding the flowpath member; and an annular centering spring disposed between the stationary structure and the flowpath member, the centering spring urging the flowpath member towards a centered position within the stationary structure.
52 citations
Patent•
28 May 2010TL;DR: A turbine shroud for a gas turbine engine includes an arcuate turbine segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces as mentioned in this paper.
Abstract: A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.
50 citations