Reduced diameter annular combustor

Claim 2

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.

Claim 3

A combustor as set forth in claim 1, wherein said first and second segmented openings are oppositely curved.

Claim 4

A combustor as set forth in claim 1, wherein said first and second segmented openings are curved in the same direction.

Claim 5

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.

Claim 6

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.

Claim 7

An annular combustor as set forth in claim 4, wherein said first and second segmented openings are curved in the same direction.

Claim 8

An annular combustor as set forth in claim 5, wherein each of said first and second segmented openings are disposed respectively radially inwardly and outwardly of their associated nozzle in relation to the engine centerline.

Claim 9

An annular combustor as set forth in claim 6, wherein said first and second segmented openings are formed on arcs concentric to the engine centerline.

Claim 10

An annular combustor as set forth in claim 7, wherein each of said first and second segmented openings have circumferential lengths longer than that of their associated nozzle.

Claim 11

An annular combustor as set forth in claim 4, wherein said first and second segmented openings are oppositely curved.

Claim 12

An annular combustor as set forth in claim 9, wherein each of said first and second segmented openings are disposed respectively radially inwardly and outwardly of their associated nozzle in relation to the engine centerline.

Claim 13

An annular combustor as set forth in claim 10, wherein each of said first and second segmented openings have circumferential lengths longer than that of their associated nozzle.

Claim 14

An annular combustor as set forth in claim 11, wherein each of said first and second segmented openings are disposed circumferentially symmetric to a radial line between the engine centerline and the center of the associated nozzle.

Claim 15

An annular combustor as set forth in claim 11, wherein each of said first and second segmented openings are disposed circumferentially asymmetric to a radial line between the engine centerline and the center of the associated nozzle.

Claim 16

An annular combustor as set forth in claim 13, wherein said first and second segmented openings are offset circumferentially in opposite directions relative to said radial line.

Claim 17

An annular combustor as set forth in claim 10, wherein said first and second arcuately segmented openings are formed on arcs concentric to the engine centerline axis.

Claim 18

An annular combustion as set forth in claim 10 wherein said second segmented openings are formed on arcs of equal radius to said first segmented openings.

Claim 19

An annular combustor as set forth in claim 4, further including a circular swirler closely surrounding each of said nozzles for directing another supply of primary airflow swirling in a direction complementary to the direction of swirl created by said first and second sets of vanes.