Gas turbine combustor

Patent metadata

Field	Value
Publication number	US-9777925-B2
Application number	US-201414531156-A
Country	US
Kind code	B2
Filing date	Nov 3, 2014
Priority date	Nov 5, 2013
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions.
The gas turbine combustor includes: a cylindrical combustion chamber that burns combustion air and fuel to thereby produce combustion gas; an outer casing disposed concentrically on an outside of the combustion chamber; an end cover disposed at an upstream side end portion of the outer casing; an annular passage formed by an outer peripheral surface of the combustion chamber and an inner peripheral surface of the outer casing, the annular passage allowing the combustion air to flow therethrough; and a passage formed inside a combustion chamber wall between the outer peripheral surface and an inner peripheral surface of the combustion chamber, the passage having a U-shape turned sideways and having ends disposed on an upstream side in a transverse cross-sectional view, in which the passage includes a first passage that extends in parallel with an axial direction of the combustion chamber and has a supply hole on a first end side thereof, the supply hole communicating with an outside of the combustion chamber wall, and a second passage that has a second end side communicating with a second end side of the first passage and has a jet hole on a first end side thereof, the jet hole communicating with an inside of the combustion chamber wall.

First claim

What is claimed is:

1. A gas turbine combustor comprising:
a cylindrical combustion chamber that burns combustion air and fuel to thereby produce combustion gas;
an outer casing disposed concentrically on an outside of the cylindrical combustion chamber;
an end cover disposed at an upstream side end portion of the outer casing;
an annular passage formed by an outer peripheral surface of the cylindrical combustion chamber and an inner peripheral surface of the outer casing, the annular passage allowing the combustion air to flow therethrough; and
a passage formed inside a combustion chamber wall between the outer peripheral surface and an inner peripheral surface of the cylindrical combustion chamber, the passage having a U-shape along a circumferential direction of the cylindrical combustion chamber and having ends disposed on an upstream side in a transverse cross-sectional view; and
a transition piece disposed on a downstream side of the combustion chamber, the transition piece receiving a downstream end of the combustion chamber fitted therewith so as to be internally inserted therein, and
a passage structure, in communication with the combustion air, including the passage, the passage further comprising a first passage and a second passage, wherein the first passage and the second passage are formed on a single circumferential plane inside the combustion chamber wall on the downstream end of the combustion chamber internally inserted into the transition piece,
wherein the first passage extends in parallel with an axial direction of the combustion chamber and has a supply hole on a first end side of the first passage, the supply hole communicating with an outside of the combustion chamber wall, and
the second passage communicating with a second end side of the first passage and has a jet hole on a first end side of the second passage, the jet hole communicating with an inside of the combustion chamber wall, and
part of the combustion air enters the supply hole and flows through the first passage in a direction identical to a flow direction of the combustion gas and thereafter turns back in the second passage to thereby flow in a direction opposite to the flow direction of the combustion gas before jetting out into the inside of the combustion chamber through the jet hole.

2. The gas turbine combustor according to claim 1 , wherein the first passage of the passages has a length longer than a length of the second passage.

3. The gas turbine combustor according to claim 1 , wherein the jet hole is formed radially in the combustion chamber between the first passage through which part of the combustion air that has flowed in through the supply hole flows in the direction identical to the flow direction of the combustion gas and the second passage through which the part of the combustion air that has flowed in through the supply hole turns back to thereby flow in the direction opposite to the flow direction of the combustion gas.

4. The gas turbine combustor according to claim 1 , wherein the first passage and the second passage are formed to be inclined obliquely with respect to the axial direction of the combustion chamber.

5. The gas turbine combustor according to claim 1 , further comprising:
a plurality of passage structures formed in a circumferential direction inside the combustion chamber wall, each of the passage structures including the passage having the first passage and the second passage and allowing part of the combustion air to flow therethrough.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Hirata Yoshitaka
• Yoshida Shohei
• Uruno Tomoki
• Hayashi Akinori
• Takahashi Hirokazu

Classifications

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05B2260/20

  Heat transfer, e.g. cooling · CPC title