초록 ▼

A gas turbine shroud ring segment assembly (36) with an outer structural block (32A) having cooling channels (72) between inlets (60) on a front face and outlets (74, 76) on a front hanger rail (48). The outlets may be positioned on a radially inner surface (77) of the front rail for impingement and

A gas turbine shroud ring segment assembly (36) with an outer structural block (32A) having cooling channels (72) between inlets (60) on a front face and outlets (74, 76) on a front hanger rail (48). The outlets may be positioned on a radially inner surface (77) of the front rail for impingement and forced convection cooling of backsides of radially inner front lips (44) of adjacent shroud ring segments (30A, 30B) mounted on front and rear rails (48, 50) of the block. The outlets may enter a pocket (86) on the inner surface configured to allow coolant flow in all positions of the ring segments (32A, 32B). The cooling channel may form a main channel (72A) and tributary channels (72B, 72C). These channels may be drilled upward from the rail to the inlet. The tributaries may have offset intersections (72E, 72D) with the main channel.

대표청구항 ▼

1. An outer structural block arranged to support a shroud ring assembly of a gas turbine engine, the outer structural block comprising: a front hanger rail including a front face and a radially inner surface and arranged to at least partially support the shroud ring assembly; anda cooling channel ar

1. An outer structural block arranged to support a shroud ring assembly of a gas turbine engine, the outer structural block comprising: a front hanger rail including a front face and a radially inner surface and arranged to at least partially support the shroud ring assembly; anda cooling channel arranged to direct a flow of fluid from an inlet formed in the front face to a first outlet formed in the radially inner surface, wherein the cooling channel comprises: a main channel;first and second tributary channels branching from respective first and second intersections on the main channel to the first outlet and to a second outlet respectively; anda plug positioned in the main channel to block the main channel downstream of the intersections, and wherein the first and second tributary channels each have a smaller diameter than the main channel, and the first and second intersections are offset from each other along a length of the main channel by a distance of at least one diameter of the main channel. 2. The outer structural block of claim 1, wherein the first outlet is directed toward a backside of a radially inner front lip of a shroud ring segment when the shroud ring segment is mounted on a mounting device, wherein the radially inner front lip extends forward of a front perimeter of a structural frame of the shroud ring segment and borders a combustion gas flow. 3. The outer structural block of claim 2, wherein the first outlet is directed toward a backside of a front corner of the radially inner front lip of the shroud ring segment. 4. The outer structural block of claim 1, wherein the first outlet and the second outlet are directed toward first and second adjacent radially inner front lips of respective first and second shroud ring segments engaged with the front hanger rail, wherein the first and second adjacent radially inner front lips extend forward of a front perimeter of a structural frame of the first and second shroud ring segments, and said first outlet and second outlet are located effective to impingement cool said first and second adjacent radially inner front lips. 5. An outer structural block for a shroud ring assembly of a gas turbine engine, comprising: a shroud ring segment mounting device;a cooling channel comprising a first outlet on a radially inner surface of a fore element of the shroud ring segment mounting device; anda second outlet of the cooling channel, wherein the first and second outlets are directed toward first and second adjacent radially inner front lips of respective first and second shroud ring segments when said shroud ring segments are mounted on the shroud ring segment mounting device, wherein the first and second adjacent radially inner front lips extend forward of a front perimeter of a structural frame of the shroud ring segment, and said first and second outlets are located effective to impingement cool said first and second adjacent radially inner front lips, wherein the fore element of the mounting device comprises a circumferentially oriented fore rail, the cooling channel comprises a coolant entrance on a front surface of the outer structural block, and the first and second outlets open into a pocket comprising a depressed area on a radially inner surface of the fore rail. 6. The outer structural block of claim 5, wherein the depressed area comprises a bounding wall that is open to an aft side of the fore rail, wherein a coolant fluid can escape aft from the pocket when said first and second adjacent radially inner front lips are adjacent and cover the pocket. 7. The outer structural block of claim 5, wherein the depressed area comprises a bounding wall, a front portion of which is open to a front side of the fore rail or is disposed forward of a front edge of the first and second adjacent radially inner front lips, wherein a coolant fluid can escape forward from the pocket and provide film cooling to the first and second adjacent radially inner front lips when said first and second adjacent radially inner front lips are adjacent and are against the inner surface of the fore rail. 8. The outer structural block of claim 5, wherein the depressed area comprises a substantially uniform shallow depth not greater than twice a diameter of either one of the first or second outlets. 9. In a ring segment assembly for a gas turbine engine comprising an outer structural block configured to connect to a casing of the engine and a plurality of inner ring segment components configured for adjacent engagement to the outer structural block via a forward hook arrangement and a rearward hook arrangement on the structural block, an improvement comprising: a cooling channel comprising an inlet end on a forward face of the outer structural block and an outlet end proximate the forward end hook arrangement, the cooling channel configured to pressurize a gap between forward end corners of adjacent inner ring segment components when the gas turbine engine is operated, wherein the cooling channel includes a second opening that cooperates with the outlet end to impinge cooling fluid onto the adjacent forward end corners of the respective adjacent inner ring segment components, and wherein the second opening and the outlet end open into a pocket formed as a depression in a surface of the outer structural block. 10. The improvement of claim 9, wherein the depression is open to a front or aft side of the forward hook arrangement.