Staged fuel and air injection in combustion systems of gas turbines
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United States of America Patent
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Jun 12, 2018
Issued Date -
Jun 22, 2017
app pub date -
Dec 22, 2015
filing date -
Dec 22, 2015
priority date (Note) -
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status (Latency Note)
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Abstract
A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath; a compressor discharge cavity; a staged injector; stator blade airfoils extending between inboard and outboard sidewalls; and a first and second coolant flowpath. The first coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the inboard sidewall; an outtake section including a downstream port connected to the staged injector and an upstream port formed through the outboard sidewall; and a cooling circuit through the airfoil. The second coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the outboard sidewall; an outtake section that comprises a downstream port connected to the staged injector and an upstream port formed through the inboard sidewall; and a cooling circuit through the airfoil.
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