Compliant shroud designs with variable stiffness
AssigneeGeneral Electric Company
InventorsRavindra Shankar Ganiger, Praveen Sharma, Jeffrey D. Carnes, Herbert Chidsey Roberts
Life of this patent
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Abstract
Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
Claims20
A shroud assembly for a gas turbine engine, the shroud assembly comprising:
- an outer wall;
- a first shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a first shroud pad, a first angular bend between the first end and the second end of the first shroud arm, further including a first straight portion between the first end and the first angular bend, and a second straight portion between the first angular bend and the second end, the first angular bend formed at an intersection of the first straight portion and the second straight portion;
- and
- a second shroud arm having a third end and a fourth end, the third end to couple to the outer wall and the fourth end to couple to the first shroud pad, a second angular bend between the third end and the fourth end of the second shroud arm, further including a third straight portion between the third end and the second angular bend, and a fourth straight portion between the second angular bend and the fourth end, the second angular bend formed at an intersection of the third straight portion and the fourth straight portion, wherein the shroud assembly includes at least one air-damping hole, the at least one air-damping hole located in at least one of the outer wall or the second shroud arm.
A gas turbine engine, comprising:
- a compressor including a compressor casing and at least one compressor blade;
- a combustion section;
- a turbine including a turbine casing and at least one turbine blade;
- a shaft to rotatably couple the compressor and the turbine;
- and
- a shroud assembly for at least one of the compressor or the turbine, the shroud assembly including:
- an outer wall;
- a first shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a first shroud pad;
- and
- a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, wherein the shroud assembly includes at least one air-damping hole, the at least one air-damping hole located in at least one of the outer wall or the second shroud arm.
A shroud apparatus comprising:
- first means for reducing blade damage having a first end and a second end, the first end of the first means to couple to second means of the shroud apparatus and the second end to couple to third means;
- and
- the second means to provide support of the shroud apparatus;
- the third means to cushion a blade;
- fourth means to cushion the blade;
- and
- fifth means for reducing blade damage having a first end and a second end, the first end to couple to the second means and the second end to couple to the fourth means, wherein the shroud apparatus includes at least one air-damping hole, the at least one air-damping hole located in at least one of the second means or the fifth means.
Dependencies are inferred from the claim text.