GAS TURBINE COMBUSTOR AND GAS TURBINE

WIPO Patent Application WO/2017/154900

A1

A gas turbine combustor and a gas turbine, wherein there are provided a combustor outer cylinder (41), a combustor inner cylinder (42), a pilot nozzle (53) and a main nozzle (56) disposed in the combustor inner cylinder (42), an air channel (51) provided between the combustor outer cylinder (41) and the combustor inner cylinder (42), and pegs (58, 71) serving as a second fuel injection unit disposed in the air channel (51). The pegs (58, 71) are disposed in a curved part (41b) in communication with the combustor inner cylinder (42) on the downstream side of the air channel (51), and are disposed so that the base end part is supported on the inner surface of the curved part (41b), the tip part extends towards the combustor inner cylinder (42) side, and the longitudinal center line (O) is inclined with respect to a perpendicular line (P) orthogonal to a tangent (T) of the curved surface of the combustor outer cylinder (41) by a predetermined angle (θ) on the downstream side (or the upstream side) with respect to the flow direction of compressed air A flowing through the air channel (51).

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JP2010159757	METHOD AND APPARATUS TO FACILITATE COOLING OF DIFFUSION TIP WITHIN GAS TURBINE ENGINE
JP2005233574	COMBUSTOR

FUKUBA SHINICHI (JP)
MIYAMOTO KENJI (JP)
SAITO KEIJIRO (JP)
TAKIGUCHI SATOSHI (JP)

PCT/JP2017/008996

September 14, 2017

March 07, 2017

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MITSUBISHI HEAVY IND LTD (JP)

F23R3/28; F23R3/30

JP2009192175A	2009-08-27
JPH09184629A	1997-07-15
JP5524407B2	2014-06-18
JP2013139967A	2013-07-18
JPH08135970A	1996-05-31
JPH1047679A	1998-02-20

See also references of EP 3428536A4

SAKAI INTERNATIONAL PATENT OFFICE (JP)

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