Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages

Patent metadata

Field	Value
Publication number	US-10125992-B2
Application number	US-201414540123-A
Country	US
Kind code	B2
Filing date	Nov 13, 2014
Priority date	Nov 15, 2013
Publication date	Nov 13, 2018
Grant date	Nov 13, 2018

Abstract

A gas turbine combustor includes a plurality of fuel nozzles, a premixing plate, and a plurality of annular flow sleeves. The plurality of annular flow sleeves includes an inner annular flow sleeve and an outer annular flow sleeve. The plurality of annular flow sleeves is formed to divide an airflow passage into a plurality of flow passages including an inner and an outer circumferential flow passages. The airflow passage is formed around the plurality of fuel nozzles. The airflow passage extends from an upstream side of the plurality of fuel nozzles to fuel injecting ports of the fuel nozzles. The plurality of annular flow sleeves rectifies a flow of air in each of the flow passages and guiding the flow of air to the fuel injecting ports of the fuel nozzles.

First claim

What is claimed is:

1. A gas turbine combustor comprising:
a plurality of fuel nozzles concentrically arranged in a first multi-array in a radial direction with respect to a centerline of the first multi-array, and spaced in a circumferential direction with respect to the centerline of the first multi-array, and having a plurality of fuel injecting ports formed to axially open with respect to the centerline of the first multi-array at a plurality of respective tip ends of the plurality of fuel nozzles;
a premixing plate in which are formed a plurality of premixing passages each positioned at a downstream side of a corresponding one of the plurality of fuel nozzles and spaced in the circumferential direction and concentrically arranged in a second multi-array in the radial direction to axially align with each of the plurality of fuel nozzles, injected fuel from the plurality of fuel nozzles being mixed with air in the plurality of premixing passages before being supplied to a combustion chamber and burnt therein; and
a plurality of annular flow sleeves including an inner annular flow sleeve and an outer annular flow sleeve and arranged at an upstream side of the plurality of premixing passages and formed to extend from an upstream side of an airflow passage around the plurality of fuel nozzles up to the plurality of fuel injecting ports of the plurality of fuel nozzles, wherein
the plurality of annular flow sleeves are configured to divide the airflow passage around the plurality of fuel nozzles at the upstream side of the plurality of premixing passages, into a plurality of flow passages including an inner circumferential flow passage and an outer circumferential flow passage for respective radial arrays from a plurality of radial arrays of the plurality of fuel nozzles concentrically arranged, and
wherein a first radial array from the plurality of radial arrays is disposed radially inward of a second radial array from the plurality of radial arrays, and
the plurality of annular flow sleeves rectifying a flow of air in each of the plurality of flow passages and guiding the flow of air to the plurality of fuel injecting ports of the plurality of fuel nozzles.

2. The gas turbine combustor according to claim 1 , wherein:
sizes and shapes of the plurality of annular flow sleeves are determined so that a mixture ratio of air and fuel injected from the plurality of fuel nozzles takes a predetermined value in each of the plurality of flow passages formed by the plurality of annular flow sleeves.

3. The gas turbine combustor according to claim 1 , wherein:
the plurality of annular flow sleeves comprise the inner annular flow sleeve and the outer annular flow sleeve,
the inner annular flow sleeve guiding air to only a first portion of the plurality of fuel injecting ports of the plurality of fuel nozzles positioned at an inner circumferential side,
the outer annular flow sleeve guiding air to a second portion of the plurality of fuel injecting ports of the plurality of fuel nozzles positioned at an outer circumferential side,
an extension of the outer annular flow sleeve that extends toward the upstream side of the plurality of premixing passages is shorter than an extension of the inner annular flow sleeve, the outer annular flow sleeve being reduced in outside diameter.

4. The gas turbine combustor according to claim 1 , wherein:
the plurality of annular flow sleeves are configured to each have a linear shape when viewed in axial section with respect to the centerline of the first multi-array, thereby reducing frictional resistance of air which flows along the plurality of annular flow sleeves.

5. The gas turbine combustor according to claim 1 , wherein:
a plurality of protruding vanes spaced from each other in the circumferential direction are disposed on an inner circumferential surface of at least one of the plurality of annular flow sleeves near a downstream end of the at least one of the plurality of annular flow sleeves, and
the plurality of protruding vanes rectify a property of air flowing along the at least one of the plurality of annular flow sleeves, and guide the rectified flow of air to the plurality of fuel injecting ports of the plurality of fuel nozzles positioned in respective flow passages from the plurality of flow passages.

6. The gas turbine combustor according to claim 5 , wherein:
at least one of the plurality of premixing passages is inclined relative to an axial direction with respect to the centerline of the first multi-array, and the plurality of protruding vanes are mounted to be inclined relative to the axial direction according to the inclination of the at least one of the plurality of premixing passages, thereby imparting a swirling angle to combustion air before the combustion air enters the at least one of the plurality of premixing passages.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Wada Yasuhiro
• Sasao Toshifumi
• Saito Takeo

Classifications

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/26

  Controlling the air flow · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23D11/40

  Mixing tubes; Burner heads · CPC title

• F23R3/04

  Air inlet arrangements · CPC title