Blade outer air seal with circumferential hook assembly

1. A gas turbine engine comprising:

a compressor section and a turbine section, said turbine section including at least one rotor and at least one blade extending radially outwardly from said rotor to a radially outer tip;

a blade outer air seal assembly including a plurality of blade outer air seals, positioned radially outwardly of said radially outer tip of said blade, each said blade outer air seal having forward and aft hooks, and said forward and aft hooks being supported on forward and aft seal hooks of an attachment block, said forward and aft seal hooks of said attachment block both facing forwardly;

said attachment block is supported on forward and aft case hooks on a static casing, with said forward and aft case hooks on said static casing both facing rearwardly;

said blade outer air seal forward and aft hooks extending at angles relative to an upper surface of a web that is between 20 and 70 degrees, each of said angles are measured as an averaged position along a length of the hook measured relative to an axis taken parallel to a rotational axis of said gas turbine engine;

wherein said blade outer air seal is formed of a plurality of laminate layered with a central web formed of a plurality of laminate members including an inner reinforcement member, and an outer overwrap that wraps around said inner reinforcement member, and radially outwardly and across said forward and aft hooks, and said inner reinforcement member not forming a portion of said blade outer air seal forward and aft hooks;

wherein said plurality of laminate members have a fibrous woven structure;

wherein there are hook reinforcement plies positioned to define each of said blade outer air seal forward and aft hooks, and radially outward of said inner reinforcement member, and there being inner front and aft plies positioned partially within each of said blade outer air seal forward and aft hooks, and extending outwardly of each of said blade outer air seal forward and aft hook to be radially outward of said inner reinforcement member;

wherein spaces are defined radially between said hook reinforcement plies, said inner reinforcement member, and each said inner forward and aft plies and loose fibers are received within said spaces;

wherein wedge seals are positioned across circumferential gaps between a plurality of said blade outer air seals;

wherein said attachment block has a forward case mount hooks and an aft case mount hook, and said attachment block being supported on a forward case hook and an aft case hook of a static casing within the engine, said aft case mount hook on said attachment block and said forward case mount hook on said attachment block facing in a first common axial direction, and said forward case hook and said aft case hook facing in a second common axial direction which is opposed to said first common axial direction; and

wherein said forward case mount hook and said aft case mount hook being circumferentially offset and said forward case hook and said aft case hook being circumferentially offset, and said forward case mount hooks on said attachment blocks being offset from said aft case hooks on said static casing, such that said forward case mount hooks on said attachment blocks can move axially circumferentially intermediate said aft case hooks on said static casing during an assembly.

2. The gas turbine engine as set forth in claim 1 , wherein said inner reinforcement member extending between a first end and a second end, with said first and second ends of said inner reinforcement member both being remote from said forward and aft hooks of said blade outer air seal, said hook reinforcement plies extending between a first end and a second end, with said first end of said hook reinforcement plies being in one of said blade outer air seal forward and aft hooks, said second end of said hook reinforcement plies being in the other of said blade outer air seal forward and aft hooks, said inner front and aft plies each extending from a first end in one of said blade outer air seal forward and aft hooks, and to a second end of said inner front and aft plies being positioned remotely from said blade outer air seal forward and aft hooks, and radially outward of said inner reinforcement member, and said outer over wrap extending to form radially outer and radially inner portions of each of said blade outer air seal forward and aft hooks, and radially inner and radially outer portions of said central web, and on opposed axial sides of said central web relative to blade outer air seal forward and aft hooks.

3. A method of assembling a blade outer air seal assembly into a gas turbine engine comprising the steps of:

(a) providing a plurality of blade outer air seals having forward and aft hooks extending at angles relative to an upper surface of a web that is between 20 and 70 degrees;

(b) providing forward and an aft case mount hooks on an attachment block, and forward and said aft case mount hooks on said attachment blocks facing a first common axial direction; and

(c) assembling the plurality of blade outer air seals and at least one wedge seal that is circumferentially intermediate to said forward and aft hooks and sealing gaps that are situated between each one of the plurality of blade outer air seals to form an intermediate product; and

(d) sliding said intermediate product circumferentially within a plurality of attachment blocks; and then

(e) moving said forward and aft case mount hooks on said attachment blocks onto forward and aft case hooks on a static casing, said static casing extending as a whole hoop structure about an axis of rotation of the gas turbine engine with forward and aft case hooks on said static casing facing a second common axial direction, which is opposed to said first common axial direction, said forward case mount hooks on said attachment blocks being offset from said aft case hooks on said static casing, such that said forward case mount hooks on said attachment blocks can move axially circumferentially intermediate said aft case hooks on said static casing during the step (e);

wherein the sliding of step (a) is generally in a circumferential direction and the moving of step (e) is generally in a forward direction.

4. The gas turbine engine as set forth in claim 1 , wherein a radially outer surface of each of said blade outer air seal forward and aft hooks is curved and without sharp corners.