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Sector staging combustor

A staged combustion and segmental technology, applied in the direction of burners, combustion chambers, combustion equipment, etc., can solve complex problems

Inactive Publication Date: 2008-07-09
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, such pressurized injectors are much more complex than blown injectors and require a more powerful fuel pump to provide adequate fuel pressure during start-up and the aforementioned idle conditions

Method used

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  • Sector staging combustor
  • Sector staging combustor
  • Sector staging combustor

Examples

Experimental program
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Embodiment Construction

[0022] exist figure 1 Schematically shown in is a gas turbine engine 10 specifically configured for use in a land vehicle (not shown) to provide propulsion power therefor. The engine is axisymmetric about a longitudinal or axial centerline axis 12 and includes an inlet 14 at an upstream end to receive ambient air 16 .

[0023] Next to the inlet is a multi-stage axial centrifugal compressor 18 which pressurizes the air 16 , from which the air 16 is then discharged to a surrounding recuperator or heat exchanger 20 . The compressor discharge air is heated in a recuperator, as further described below, and returned to the upstream end of the annular combustor 22 as appropriate.

[0024] Fuel 24 is mixed with pressurized air 16 and ignited in a combustor to generate therein hot combustion gases 26 which are discharged from a downstream outlet port to a single stage high pressure turbine (HPT) 28 . The rotor disk of the HPT 28 is suitably connected to a first rotor or shaft 30 whic...

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Abstract

A combustor (22) includes outer and inner liners (40,42) joined together by a dome (44) to define a combustor chamber (46). A row of air swirlers (48) is mounted in the dome and includes corresponding main fuel injectors (50) for producing corresponding fuel and air mixtures. Pilot fuel injectors (52) fewer in number than the main injectors (50) are mounted in the dome between corresponding ones of the swirlers (48). Staged fuel injection from the pilot and main injectors is used for starting the combustor during operation.

Description

[0001] The United States Government has certain rights in this invention under Contract No. DAAE07-00-C-N086 awarded by the Department of the Army. technical field [0002] The present invention relates generally to gas turbine engines, and more particularly, the present invention relates to land vehicle turbine engines. Background technique [0003] In a gas turbine engine, air is pressurized in a compressor and mixed with fuel in a combustor to produce hot combustion gases from which energy is extracted by passing through downstream turbine stages. A high pressure turbine (HPT) follows the combustor and is connected by a first rotor or shaft to an upstream compressor, usually comprising multiple stages. A low pressure turbine (LPT) is disposed downstream of the HPT and generates output power for the second rotor or drive shaft. [0004] In a typical turbofan engine, the LPT is connected to a large fan ahead of the compressor and is used to generate the propulsive impulse ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/34F02C9/32F02C9/48F02C7/22F02C5/02F02C7/26
CPCF23R3/343F23D2900/00014
Inventor S·J·霍维尔J·C·雅各布森T·P·麦卡弗里B·F·巴恩斯
Owner GENERAL ELECTRIC CO
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