초록 ▼

An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the roto

An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing.

대표청구항 ▼

1. A seal assembly for use in a turbine engine including a compressor casing that at least partially circumscribes a rotor, said seal assembly comprising a plurality of arcuate seal segments configured to be at least partially inserted into a groove defined in the compressor casing to substantially

1. A seal assembly for use in a turbine engine including a compressor casing that at least partially circumscribes a rotor, said seal assembly comprising a plurality of arcuate seal segments configured to be at least partially inserted into a groove defined in the compressor casing to substantially seal a gap defined between the casing and the rotor, wherein each of said plurality of seal segments comprises a radially inner projection, a radially outer projection, and a neck portion extending therebetween and wherein said groove is configured to receive an entirety of said radially inner projection, said radially outer projection and said neck portion wherein each of said plurality of seal segments further comprises a tool acceptor configured to facilitate removal of said seal segment from the compressor casing, wherein said tool acceptor comprises a circumferentially-oriented opening defined in an end surface of each of said plurality of seal segments. 2. An assembly in accordance with claim 1, wherein said groove includes at least one hook portion configured to retain each of said plurality of arcuate seal segments within said groove. 3. An assembly in accordance with claim 1, wherein said seal assembly further comprises an anti-rotation device coupled to the compressor casing, said anti-rotation device configured to prevent said plurality of arcuate seal segments from shifting circumferentially within said groove. 4. An assembly in accordance with claim 1, wherein each of said plurality of seal segments further comprises at least one cutout sized to receive at least a portion of a biasing mechanism therein. 5. An assembly in accordance with claim 4, wherein said biasing mechanism comprises one of a coil spring and a wave spring. 6. An assembly in accordance with claim 1, wherein said each of said plurality of seal segments further comprises a sealing surface extending a full circumferential length and a full axial length along each said seal segment, said sealing surface extends a distance above and below a radially inner surface of the compressor casing when said seal segment is coupled the compressor casing. 7. An assembly in accordance with claim 6, wherein said sealing surface comprises one of an abradable seal surface, a honeycomb seal surface, and a brush seal surface. 8. A method of sealing a compressor in a turbine engine, said method comprising: forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor housed within the casing;coupling the compressor casing to the rotor such that the compressor casing extends circumferentially about the rotor;inserting a plurality of arcuate seal segments into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap defined between the rotor and the compressor casing, wherein each of said plurality of seal segments comprises a radially inner projection, a radially outer projection, and a neck portion extending therebetween, and wherein inserting comprises inserting an entirety of said radially inner projection, said radially outer projection, and said neck portion into the groove; andinserting a tool into a tool acceptor of each of the first plurality of arcuate seal segments such that when a pulling force is exerted on the tool, each arcuate seal segment is removed from the compressor casing as the lower portion of the compressor casing at least partially circumscribes the rotor, wherein the tool acceptor includes a circumferentially-oriented opening defined in an end surface of each of the plurality of seal segments. 9. A method in accordance with claim 8, wherein said each of said plurality of seal segments further comprises a sealing surface extending a full circumferential length and a full axial length along each said seal segment, said sealing surface extends a distance above and below a radially inner surface of the compressor casing when said seal segment is coupled to the compressor casing. 10. A method in accordance with claim 9, wherein said sealing surface comprises one of an abradable seal surface, a honeycomb seal surface, and a brush seal surface. 11. A method in accordance with claim 8 further comprising coupling an anti-rotation device to the compressor casing to prevent said plurality of arcuate seal segments from shifting circumferentially within compressor casing groove. 12. A method in accordance with claim 8 further comprising replacing the plurality of arcuate seal segments for each stage of the compressor, the method comprising: removing an upper portion of the compressor casing to provide access to a first plurality of seal segments within the upper portion and a lower portion of the compressor casing;removing an anti-rotation device to allow each of the first plurality of arcuate seal segments to shift within the compressor casing;inserting a tool into a tool acceptor of each of the first plurality of arcuate seal segments such that when a pulling force is exerted on the tool, each arcuate seal segment is removed from the compressor casing as the lower portion of the compressor casing at least partially circumscribes the rotor;inserting a second plurality of arcuate seal segments into the upper portion and the lower portion of the compressor casing;recoupling the anti-rotation device to the compressor casing; andrecoupling the upper portion of compressor casing to the lower portion of compressor casing. 13. A turbine engine system comprising: a rotor;a compressor including a plurality of stages sequentially spaced on the rotor along a longitudinal axis;a compressor casing that at least partially circumscribes the rotor;a plurality of arcuate seal segments for each of the plurality of stages, wherein each of said plurality of arcuate seal segments is configured to slidably couple to the compressor casing without removing the rotor from the compressor casing to substantially seal a gap defined between the casing and the rotor at each stage, wherein each of said plurality of seal segments further comprises a tool acceptor configured to facilitate removal of said seal segment from said compressor casing, wherein said tool acceptor comprises a circumferentially-oriented opening defined in an end surface of each of said plurality of seal segments. 14. A turbine engine system in accordance with claim 13, wherein said compressor casing comprises a groove defined therein and each of said plurality of seal segments comprises a radially inner projection, a radially outer projection, and a neck portion extending therebetween, wherein said groove is configured to receive an entirety of said radially inner projection, said radially outer projection, and said neck portion. 15. A turbine engine in accordance with claim 13, wherein said each of said plurality of seal segments further comprises a sealing surface extending a full circumferential length and a full axial length along each said seal segment, said sealing surface extends a distance above and below a radially inner surface of the compressor casing when said seal segment is coupled the compressor casing. 16. A turbine engine system in accordance with claim 15, wherein said sealing surface comprises one of an abradable seal surface, a honeycomb seal surface, and a brush seal surface. 17. A turbine engine system in accordance with claim 15, wherein a sealing surface having greater restorative capabilities is utilized in the aft stages of the engine and a sealing surface having reduced restorative capabilities is utilized in the forward stages of the engine.