JP2007064625A5

JP2007064625A5 -

Info

Publication number: JP2007064625A5
Application number: JP2006332911A
Authority: JP
Filing date: 2006-12-11
Publication date: 2009-07-23
Anticipated expiration: 2023-06-19

Claims

In a gas turbine combustor that mixes and burns fuel with combustion air introduced from a compressor and supplies the generated combustion gas to a gas turbine.
A first fuel nozzle that ejects fuel;
A mixing chamber wall forming a mixing chamber downstream of the first fuel nozzle ;
And sky pores provided in front Symbol mixing chamber wall,
And a second fuel nozzle provided so as to face the front Symbol air holes on the outer peripheral side of the mixing chamber wall,
The gas turbine combustor, wherein the air hole and the second fuel nozzle are configured to promote generation of a swirling flow in the mixing chamber .

In a gas turbine combustor that mixes and burns fuel with combustion air introduced from a compressor and supplies the generated combustion gas to a gas turbine.
A first fuel nozzle that ejects fuel;
Provided around the first fuel nozzle, a mixing chamber wall thereof toward the ejection direction has a flared shape, to form a mixing chamber therein,
And sky pores provided in front Symbol mixing chamber wall,
And a second fuel nozzle provided so as to face the front Symbol air holes on the outer peripheral side of the mixing chamber wall,
The gas turbine combustor, wherein the air hole and the second fuel nozzle are configured to promote generation of a swirling flow in the mixing chamber .

In a gas turbine combustor that mixes and burns fuel with combustion air introduced from a compressor and supplies the generated combustion gas to a gas turbine.
A first fuel nozzle that ejects fuel;
Provided around the first fuel nozzle, a mixing chamber wall thereof toward the ejection direction has a flared shape, to form a mixing chamber therein,
And sky pores provided in front Symbol mixing chamber wall,
And a second fuel nozzle provided so as to face the front Symbol air holes on the outer peripheral side of the mixing chamber wall,
A gas turbine combustor configured such that an axial center line of the first fuel nozzle does not intersect with an axial center line of the air hole .

In a gas turbine combustor that mixes and burns fuel with combustion air introduced from a compressor and supplies the generated combustion gas to a gas turbine.
A first fuel nozzle that ejects fuel;
Provided around the first fuel nozzle, a mixing chamber wall thereof toward the ejection direction has a flared shape, to form a mixing chamber therein,
And sky pores provided in front Symbol mixing chamber wall,
And a second fuel nozzle provided so as to face the front Symbol air holes on the outer peripheral side of the mixing chamber wall,
A gas turbine combustor configured so that an axis of the first fuel nozzle does not intersect with an axis of the second fuel nozzle .

4. The gas turbine combustor according to claim 3, wherein an axial center line of the air hole coincides with an axial center line of the opposing second fuel nozzle. 5.

A fuel supply method for a gas turbine combustor that mixes combustion air and fuel introduced from a compressor in a mixing chamber formed by a mixing chamber wall ,
A first fuel from the upper stream side of the mixing chamber is ejected into the mixing chamber,
The second fuel is ejected from a position outside the mixing chamber and facing the air hole provided in the mixing chamber wall, and the second fuel and combustion air are generated from the air hole to generate a swirling flow. A fuel supply method for a gas turbine combustor, wherein the fuel is introduced into the mixing chamber so as to promote the fuel.