Combustor for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10775047-B2
Application number	US-201615363414-A
Country	US
Kind code	B2
Filing date	Nov 29, 2016
Priority date	May 30, 2014
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

A combustor includes: a combustion liner having a combustion chamber formed therein; and a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide grooves that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

First claim

What is claimed is:

1. A combustor comprising:
a combustion liner having a combustion chamber formed therein; and
a fuel injector mounted to a top portion of the combustion liner and configured to inject fuel and air into the combustion chamber, the fuel injector including a fuel injection member having a plurality of fuel injection annular bodies, and an air guide member having a plurality of combustion air annular bodies that guide the air for combustion, each of the plurality of fuel injection annular bodies and each of the plurality of combustion air annular bodies being arranged concentrically and alternately about a central axis of the combustor; wherein
each of the plurality of fuel injection annular bodies includes a plurality of fuel injection holes that are open in a radial direction of the respective fuel injection annular body of the plurality of fuel injection annular bodies,
each of the plurality of combustion air annular bodies includes a plurality of air guide grooves that are formed at circumferential positions corresponding to respective fuel injection holes of the plurality of fuel injection holes, are recessed in the radial direction of a respective combustion air annular body of the plurality of combustion air annular bodies, are open in an axial direction of the plurality of combustion air annular bodies, and guide the air to the fuel jetted from the respective fuel injection holes of the respective combustion air annular body,
for each of the plurality of combustion air annular bodies, each of the plurality of air guide grooves of the respective combustion air annular body are outwardly or inwardly open in the radial direction to an exterior of the respective combustion air annular body,
each of the plurality of fuel injection annular bodies includes: a first fuel flow passage that is positioned on a combustion chamber side and is communicated with the plurality of fuel injection holes; a second fuel flow passage that is positioned on a side opposite to the combustion chamber, and is supplied with the fuel to be jetted from the plurality of fuel injection holes; and an injection nozzle configured to jet the fuel in the second fuel flow passage to a wall surface of the first fuel flow passage on the combustion chamber side, and
the fuel in the first fuel flow passage reverses direction with respect to an injection direction of the injection nozzle.

2. The combustor as claimed in claim 1 , further comprising an air-flow rectifying mechanism provided upstream of the fuel injector, and configured to cause a flow of the air supplied to the air guide member to increase in uniformity.

3. The combustor as claimed in claim 1 , further comprising a rectifying protrusion member that is provided on the central axis of the combustor and penetrates through the fuel injector so as to protrude toward the combustion chamber, the rectifying protrusion member configured to increase a stability of a flame formed by the fuel jetted from the plurality of fuel injection annular bodies.

4. The combustor as claimed in claim 3 , wherein the rectifying protrusion member includes a support portion, and a protruding portion protruding from the support portion into the combustion chamber, and has a cooling air introduction hole that is formed in the support portion to introduce the air into the rectifying protrusion member, and a cooling air discharge hole that is formed in the protruding portion to discharge the air introduced into the rectifying protrusion member to the combustion chamber.

5. The combustor as claimed in claim 1 , comprising:
a fuel supply main pipe having a multiple pipe structure, and configured to supply the fuel to the fuel injection member,
wherein the fuel supply main pipe includes a first supply passage configured to supply the fuel to a first annular body group of the plurality of fuel injection annular bodies, and a second supply passage configured to supply the fuel to a second annular body group of the plurality of fuel injection annular bodies.

6. The combustor as claimed in claim 1 , wherein the plurality of air guide grooves of the air guide member are disposed only on an upstream side in a flow direction of the air relative to the plurality of fuel injection holes.

7. The combustor as claimed in claim 1 , wherein each axial end of the plurality of air guide grooves of the plurality of combustion air annular bodies, on a side of the combustion chamber, is disposed further away from the combustion chamber than the plurality of fuel injection holes of the plurality of fuel injection annular bodies.

8. The combustor as claimed in claim 1 , wherein each of the plurality of fuel injection annular bodies has a rectangular cross-sectional outline, and the plurality of fuel injection holes are provided in an outer circumferential wall and/or an inner circumferential wall of each of the plurality of fuel injection annular bodies.

9. The combustor as claimed in claimed in claim 1 , wherein each of the plurality of combustion air annular bodies has an annular plate shape that is parallel to a plane perpendicular to the central axis of the combustor.

10. The combustor as claimed in claim 1 , wherein each of the plurality of fuel injection holes of each of the plurality of fuel injection annular bodies is configured to inject the fuel radially with respect to the central axis.

11. The combustor as claimed in claim 1 , wherein the respective combustion air annular body of the plurality of air annular bodies includes: a first air guide groove of the plurality of air guide grooves of the combustion air annular body that is outwardly open in the radial direction of the combustion air annular body; a second air guide groove of the plurality of air guide grooves of the combustion air annular body that is inwardly open in the radial direction of the combustion air annular body; and an annular body portion that circumferentially extends around a radial center of the combustion air annular body with a constant curvature, the annular body portion sandwiched between the first air guide groove and the second air guide groove in the radial direction of the annular body portion.

Assignees

• Kawasaki Heavy Ind Ltd
• B&B Agema Gmbh

Inventors

• Horikawa Atsushi
• Kazari Masahide
• Okada Kunio
• Kitajima Junichi
• Funke Harald
• Kusterer Karsten
• Ayed Anis Haj

Classifications

• F23R3/18 Primary

  Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants · CPC title

• F23C2900/9901

  Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel · CPC title

• Y02T50/678

  Aviation using fuels of non-fossil origin · CPC title

• F23D14/70 Primary

  Baffles or like flow-disturbing devices · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title