System for mounting combustor transition piece to frame of gas turbine engine
AssigneeGeneral Electric Company
InventorsDavid William Cihlar, Patrick Benedict Melton, John Drake Vanselow
Life of this patent
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Abstract
A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint.
Claims21
A system, comprising:
- a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine, wherein the combustor transition piece comprises:
- a hollow body comprising an internal flow passage extending from an upstream end portion to a downstream end portion;
- an aft frame coupled to the downstream end portion of the hollow body;
- a single aft flange coupled to a portion of the aft frame;
- and
- a mounting lug removably coupled to the single aft flange at a first joint, wherein the mounting lug is configured to removably couple to a mounting bracket at a second joint, and at least the second joint comprises a movable joint configured to enable movement of the combustor transition piece relative to the mounting bracket, wherein the movable joint comprises a rotational joint and the first joint comprise a plurality of fasteners.
A system, comprising:
- a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine;
- and
- an aft mounting system, comprising:
- a removable mounting lug;
- a first removable joint coupling the removable mounting lug to an aft portion of the combustor transition piece;
- a mounting bracket;
- and
- a second removable joint coupling the removable mounting lug to the mounting bracket, wherein a first width of the removable mounting lug is approximately 5 to 50 percent of a second width of the aft portion, and at least the second removable joint comprises a movable joint configured to enable movement of the combustor transition piece relative to the mounting bracket;
- wherein the movable joint of the second removable joint comprises a rotational joint and wherein the first removable joint comprises a plurality of removable fasteners spaced apart from one another, and the rotational joint has a rotational axis oriented crosswise relative to axes of the plurality of removable fasteners.
A system, comprising:
- an aft mounting system configured to support a combustor transition piece between a combustor and a turbine of a gas turbine engine, wherein the aft mounting system comprises:
- a removable mounting lug comprising opposite first and second end portions;
- a first joint disposed at the first end portion, wherein the first joint comprises a first removable fastener, and the first joint is configured to removably couple the removable mounting lug to a single aft flange of the combustor transition piece, wherein a first width of the removable mounting lug is approximately 5 to 50 percent of a second width of an aft portion of the combustor transition piece adjacent the single aft flange;
- and
- a second joint disposed at the second end portion, wherein the second joint comprises a rotational joint having a second removable fastener, and the second joint is configured to removably couple the removable mounting lug to a mounting bracket on the gas turbine engine.
Dependencies are inferred from the claim text.