초록 ▼

A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressuriz

A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source. The port cover extends circumferentially around the gas turbine engine and can include a portion that is anchored and an opposite portion coupled to an actuator. Movement of the actuator causes the port cover to open and close the port. Biasing members can be used to urge the port cover into one of an open and closed position against the movement of the actuator.

대표청구항 ▼

1. An apparatus comprising: a gas turbine engine having a compressor that includes a row of rotatable blades for compressing a working fluid between a first flow surface and a second flow surface of the compressor;a flow path operable to deliver an injection fluid radially inward to the compressor t

1. An apparatus comprising: a gas turbine engine having a compressor that includes a row of rotatable blades for compressing a working fluid between a first flow surface and a second flow surface of the compressor;a flow path operable to deliver an injection fluid radially inward to the compressor through an air flow port of the first flow surface;an air injection system for the compressor including a valve band extending across the air flow port and moveable in a circumferential direction relative to the gas turbine engine to selectively permit the injection fluid to flow into the compressor;wherein the valve band includes a first end that is fixed relative to the gas turbine engine,wherein the valve band moves radially to open and close the air flow port, andwhich further includes a biasing member to resist closing of the air flow port with the valve band. 2. The apparatus of claim 1, wherein the injection fluid is working fluid withdrawn from the flow path of the gas turbine engine at a location axially downstream of the air flow port and the flow path is operable to deliver the injection fluid to a tip region of the compressor. 3. The apparatus of claim 1, wherein the gas turbine engine includes a plurality of compressor stages, a plurality of air flow ports leading to the plurality of compressor stages, and a plurality of valve bands that selectively permit flow into the compressor, each of the plurality of valve bands independently operable. 4. The apparatus of claim 1, further comprising an actuator coupled to the valve band that is operable between a first position and a second position wherein actuation of the actuator causes the valve band to circumferentially move to selectively open and close the air flow port. 5. The apparatus of claim 4, wherein the actuator is a pneumatic actuator that actuates the valve band in a linear direction. 6. An apparatus comprising: a gas turbine engine having a compressor in fluid communication with a flow path structured to deliver a relatively pressurized fluid to a tip region of the compressor through a compressor opening;a valve that selectively opens and closes the compressor opening to permit the relatively pressurized fluid into the compressor, the valve including a moveable component coupled to a biasing member that urges the valve to an open position, the moveable component coupled to an actuator capable of urging the valve to a closed position,wherein the moveable component is a band that extends circumferentially around the compressor, andwherein an end portion of the band is fixed relative to the gas turbine engine. 7. The apparatus of claim 6, wherein the band is constrained by a band guide surface. 8. The apparatus of claim 6, wherein the biasing member is integral with the moveable component. 9. The apparatus of claim 6, wherein the actuator is operable to variably position the valve between an open position and a closed position. 10. The apparatus of claim 6, wherein the compressor opening is an annular opening. 11. An apparatus comprising: a gas turbine engine having a compressor;a circumferential valve including a circumferential valve band for delivering a working fluid through a flow path surface of the compressor to a bladed row of the compressor;an actuator structured to manipulate the circumferential valve between a relatively open position and a relatively closed position; andmeans for biasing the circumferential valve to one of a closed and open position, wherein the means for biasing is located radially between the flow path surface of the compressor and the circumferential valve band. 12. The apparatus of claim 11, wherein the means for biasing is integral with the circumferential valve. 13. A method comprising: operating a gas turbine engine and flowing a working fluid through a compressor flow path of a compressor to a combustor;conveying a relatively pressurized fluid toward an opening in the compressor that leads to the compressor flow path; andactuating a compressor valve by moving a valve member in a circumferential direction to selectively contact a compressor valve seat, the pressurized fluid conveyed through the opening when the valve member is not in contact with the compressor valve seat, andwhich further includes biasing the valve member to an open position with a spring. 14. The method of claim 13, wherein the actuating the compressor valve includes circumferentially moving the valve member and changing a radial distance between the valve member and the compressor valve seat to flow the relatively pressurized fluid through the opening and into the compressor. 15. The method of claim 13, wherein the valve member is a band that extends around the gas turbine engine, which further includes anchoring an end of the valve member to the gas turbine engine.