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US 5,331,805 AGranted
Reduced diameter annular combustor
AssigneeAlliedSignal Inc.
InventorsGeoffrey D. Myers, Manuel M. Cardenas, Jr.
Life of this patent
Estimating the term…
Abstract
An annular gas turbine engine combustor includes additional axial primary airflow openings, formed as arcuately segmented openings on opposite sides of each of the airblast fuel nozzles of the combustor, for reducing overall combustor diameter while maintaining flame stabilization and avoiding unacceptable thermal variations in the combustion process.
Claims17
A gas turbine engine combustor comprising:
- an axially extending combustor case having an opening for receiving pressurized airflow;
- an axially extending combustor liner disposed within said case to define a combustion chamber within said liner and an air supply passage between said case and liner, said liner having a plurality of openings along the axial length thereof to deliver airflow to the combustion chamber;
- a dome closing the forward end of said liner, the opposite aft end of said liner being open for exit of hot gas to perform useful work, said dome having first and second arcuately segmented openings therein;
- an air blast fuel nozzle secured to said dome between said first and second segmented openings for delivery of atomized fuel-air mixture to a primary zone of the combustion chamber immediately downstream of said dome;
- and
- a first set of inclined vanes extending across said first segmented opening and a second set of oppositely inclined vanes extending across said second segmented opening, whereby a swirling supply of primary airflow is introduced into said primary zone in circumferentially surrounding relation to said fuel-air mixture.
3 more elements
An annular gas turbine engine combustor comprising:
- an annular case having axially extending, concentric, inner and outer combustor casings extending circumferentially about the axis of the engine, said case receiving pressurized airflow through one axial end thereof;
- an annular combustor liner having perforated, axially extending, concentric, inner and outer liners within said case and extending circumferentially about the engine centerline, said inner and outer liners defining an annular combustion chamber therebetween receiving pressurized airflow through said perforations;
- a dome at one axial end of said lining for substantially closing said combustion chamber, the opposite axial end of said lining being open for exhaust of combustion gas products from the combustion chamber;
- a plurality of air blast fuel nozzles spaced circumferentially about and secured to said dome for delivery of atomized fuel-air mixture to a primary zone of the combustion chamber immediately downstream of said dome, said dome having separate first and second arcuately segmented openings associated with each of said nozzles;
- and
- a first set of inclined vanes extending across each of said first segmented openings, and a second set of oppositely inclined vanes extending across each of said second segmented openings, whereby a swirling supply of primary airflow is introduced into said primary zone in circumferentially surrounding relation to said fuel-air mixture issuing from each of said nozzles.
3 more elements
Dependencies are inferred from the claim text.