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|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 16 인용 특허 : 12|
A gas turbine engine includes a compressor powered by a turbine. The turbine includes a nozzle having vanes extending between outer and inner bands. Each vane includes an internal cooling plenum and a bypass tube extending through the bands. First and second manifolds surround the outer band and are disposed in flow communication with the plenums and bypass tubes, respectively. A bleed circuit joins the compressor to the manifolds for providing pressurized air thereto. A control valve modulates airflow to the first manifold and in turn through the cooli...
Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A gas turbine engine comprising: a compressor joined to a turbine for being powered thereby; said turbine including a nozzle having a row of hollow vanes extending radially between outer and inner bands, and said outer band is supported in an annular outer casing; each of said vanes having an internal cooling plenum, and a bypass tube extending through said outer and inner bands; ...