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Mixing swirler

A swirler and airflow technology, applied in the field of gas turbine engines, can solve problems such as non-optimal structures

Active Publication Date: 2009-05-20
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, variations in the dynamic pressure of the compressed air around the circumference of each swirler and around the circumference of the double annular combustor cause variations in the performance of the individual swirlers and the resulting combustor
[0011] The "nozzle-radial" configuration described above may cause uncontrolled fuel self-ignition in high-ratio engines and is therefore not the preferred configuration

Method used

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Examples

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Embodiment Construction

[0024] Figure 1 shows a portion of a typical exemplary turbofan gas turbine engine having an annular combustor 10 suitably mounted within a casing coaxially about a longitudinal or central axis 12, the combustor 10 has a radially outer liner 14 and a radially inner liner 16 whose inlet ends are suitably connected to an annular combustor cowling 18 .

[0025] The exemplary combustor is a single structure annular combustor having an inlet plenum extending axially forward from the junction of the cowl and the inner and outer liners to form an annular intake plenum on the intake side of the cowl 24 radial outer cover 20 and inner cover 22.

[0026] The engine described above has a suitable compressor 26 (such as a conventional axial multistage compressor) adapted to compress the air 28 passing therethrough downstream. Compressed air 28 flows axially downstream from the compressor through a suitable diffuser at its rear end and enters the intake plenum 24 formed between the inner ...

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Abstract

A swirler (30) has a tubular body (40) with a row of secondary radial swirl vanes (46). The tubular ferrule (52) joins the above-mentioned body at the above-mentioned secondary vane, and includes a row of primary scroll vanes (54), which are arranged axially relative to the secondary vane (46) are inclined and have a common radially outward annular inlet (56) to allow air flow to enter the tube body (40) by axial momentum generating a radially inward swirl.

Description

technical field [0001] The present invention relates generally to gas turbine engines, and more particularly to combustors therein. Background technique [0002] In a gas turbine engine, a compressor compresses air and mixes it with fuel in a combustor to burn it to produce a hot gas flow that flows downstream through a turbine that extracts energy through stages. The high pressure turbine drives the compressor, and the low pressure turbine does useful work by driving an upstream fan, such as in a typical aviation turbofan gas turbine engine. [0003] The performance of the combustor is very important to the overall performance of the gas turbine engine. Compressed air is mixed with fuel in the combustion chamber to become a mixture of fuel and air, which is then ignited and burned to produce gas. [0004] In a typical annular combustor, an array of individual carburetors in the form of swirlers and associated fuel nozzles are used. Fuel is mixed with air prior to combust...

Claims

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Application Information

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IPC IPC(8): F23R3/00F23R3/58F02C7/232F23R3/14F23R3/28
CPCY02T50/675F23R3/14Y02T50/60
Inventor M·阿尔-罗布S·P·赛托J·R·斯塔克T·-Y·屠
Owner GENERAL ELECTRIC CO