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Combustor dome assembly of a gas turbine engine having a free floating swirler

A technology of gas turbines and gas turbines, which is applied in the direction of burners, combustion chambers, combustion methods, etc., and can solve problems such as leanness and emission reduction

Active Publication Date: 2009-07-29
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Although, typical burner constructions have enough room between the swirler shrouds to install parts to enhance the double-annulus structure (e.g., add ribs, cooling holes, etc.), the current burner design still has some geometry limits, these burner configurations operate lean burn to reduce emissions

Method used

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  • Combustor dome assembly of a gas turbine engine having a free floating swirler
  • Combustor dome assembly of a gas turbine engine having a free floating swirler
  • Combustor dome assembly of a gas turbine engine having a free floating swirler

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Embodiment Construction

[0023] Referring now in detail to the drawings, wherein like parts are designated by like numerals throughout. figure 1 A combustor 10 of an exemplary gas turbine is shown with a longitudinal center axis 12 passing through it. The combustor 10 includes a combustion chamber 14 formed by an outer liner 16, an inner liner 18 and a dome plate 20 at the upstream end. Within the dome plate 20 , a plurality of fuel / air mixers 22 are circumferentially spaced from each other for feeding a mixture of fuel and air into the combustion chamber 14 . The mixture is ignited by an igniter (not shown) in the combustion chamber and forms combustion gases for driving one or more turbines downstream. More specifically, each air / fuel mixer 22 includes a fuel nozzle 24 , a swirler 26 and a deflector plate 28 .

[0024] More specifically, the dome plate 20 is circular and includes an inner portion 30, an outer portion 32, a forward surface 34 and a plurality of circumferentially spaced holes 36 (se...

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Abstract

A combustor dome assembly (10) for a gas turbine engine having a longitudinal center axis (12) passing through it, comprising: a dome formed thereon having an inner portion (30), an outer portion (32) , an annular dome plate (20) with a front surface (34) and a plurality of circumferentially spaced holes (36), wherein a radial zone (37) is formed between each adjacent hole (36); and an annular outer cover (38) connected to said outer portion (32) of said dome plate (20); an annular inner cover (44) connected to said inner portion (30) of said dome plate (20) and disposed between said front surface (34) of said dome panel (20) and said inner and outer covers (44, 38), substantially in relation to each of said dome panels (20) A swirler (26) aligned with holes (36); said swirler (26) includes a front portion (50) and a rear portion (52); wherein each of said swirlers (26) , also includes a front part (50) and a rear part (52), and is held by at least one tab member (54 / 5856 / 60) located upstream thereof, movable in radial and axial directions.

Description

technical field [0001] The present invention relates generally to a combustor dome assembly for a gas turbine, and more particularly to a combustor dome assembly having a plurality of free-floating swirlers. The swirlers are held in position between the dome plate and the inner and outer shrouds such that each swirler receives a fuel nozzle and is movable radially and axially with the nozzle. Background technique [0002] As is well known in gas turbine combustor technology, the dome section, in combination with inner and outer liners, serves to form the boundaries of the combustion chamber. The mixture of fuel and air is ignited and combusted in such a combustor, causing its products to act against the blades of the turbine and generate work through one or more shafts. An annular combustor dome allows mixers to be positioned around the circumference to allow the fuel / air mixture to enter the combustion chamber. [0003] Gas turbine combustors generally require a floating ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/60F23R3/14F23R3/42
CPCF23D2211/00F23R3/10F23R3/14F23R3/60
Inventor M·A·麦克马斯特斯J·E·汤普森G·A·茨马鲁斯蒂J·N·库珀G·E·维赫
Owner GENERAL ELECTRIC CO
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