Fuel injector and a combustion chamber
Inactive Publication Date: 2014-12-11
ROLLS ROYCE PLC +1
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- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Benefits of technology
The present invention provides a fuel injector for a combustion chamber that includes a pilot fuel injector and a main fuel injector. The pilot fuel injector includes at least one pilot air swirler, while the main fuel injector includes a main air blast fuel injector located between an inner main air swirler and an outer main air swirler. The fuel injector also includes a first air splitter and a second air splitter located between the pilot air swirler and the inner main air swirler. The ratio of the distance from the downstream end of the first air splitter to the downstream end of the second air splitter to the diameter of the downstream end of the second air splitter is in the range of 0.22 to 0.30. The pilot fuel injector and the main fuel injector are connected to separate pilot and main air swirlers, which produce separate flows of air that mix with each other and with the air flow upstream of the igniter. This allows for better control of the pilot and main fuel sprays in the combustion chamber, leading to improved engine performance.
Problems solved by technology
Conventionally gas turbine engine combustion chambers use rich burn technology, however rich burn gas turbine engine combustion chambers will not be able to achieve future nitrous oxide (NOx) emission requirements.
There have been problems with obtaining satisfactory ignition of the fuel in the combustion chamber or problems with unacceptably high temperatures of the second air splitter and unacceptably low combustion efficiency when the pilot fuel injector only is used.
Method used
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Embodiment Construction
[0030]A turbofan gas turbine engine 10, as shown in FIG. 1, comprises in flow series an intake 11, a fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and an exhaust 19. The high pressure turbine 16 is arranged to drive the high pressure compressor 14 via a first shaft 26. The intermediate pressure turbine 17 is arranged to drive the intermediate pressure compressor 13 via a second shaft 28 and the low pressure turbine 18 is arranged to drive the fan 12 via a third shaft 30. In operation air flows into the intake 11 and is compressed by the fan 12. A first portion of the air flows through, and is compressed by, the intermediate pressure compressor 13 and the high pressure compressor 14 and is supplied to the combustion chamber 15. Fuel is injected into the combustion chamber 15 and is burnt in the air to produce hot exhaust gases which flow...
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A fuel injector includes pilot and main fuel injectors. The pilot fuel injector includes at least one pilot air swirler and the main fuel injector includes a main air blast fuel injector located between inner main and outer main air swirlers. A first air splitter is located between the pilot and inner main air swirlers and a second air splitter is located between the pilot and inner main air swirlers. The first air splitter has a downstream portion converging to a downstream end. The second air splitter has a downstream portion diverging to a downstream end. The second air splitter downstream end is downstream of the first air splitter downstream end and the ratio of the distance from the first air splitter downstream end to the second air splitter downstream end to the diameter of the second air splitter downstream end is in the range of 0.22 to 0.30.
Description
FIELD OF THE INVENTION[0001]The present invention relates to a fuel injector and a combustion chamber and in particular to a lean burn fuel injector and a gas turbine engine combustion chamber.BACKGROUND TO THE INVENTION[0002]Conventionally fuel is supplied into a gas turbine engine combustion chamber via a plurality of fuel injectors. In an annular combustion chamber each fuel injector is located in a respective one of a plurality of apertures in an upstream end of the combustion chamber.[0003]One type of gas turbine engine combustion chamber is known as a rich burn combustion chamber and another type of gas turbine engine combustion chamber is known as a lean burn combustion chamber. In a lean burn type of combustion chamber the fuel and air is mixed such that the fuel to air equivalence ratio is less than one.[0004]Conventionally gas turbine engine combustion chambers use rich burn technology, however rich burn gas turbine engine combustion chambers will not be able to achieve fu...
Claims
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Patent Timeline
Login to View More IPC IPC(8): F23R3/34
CPCF23R3/343F23R3/346F23D11/107
Inventor TOON, IAN JAMESHICKS, ROBERT ANTHONYWHITEMAN, MICHAELLAZIK, WALDEMARBAGCHI, IMON-KALYAN
Owner ROLLS ROYCE PLC