US4155220A — Combustion apparatus for a gas turbine engine

Claim 1

Independent Claim 346 words

Combustion apparatus for a gas turbine engine having a housing enclosing a generally open-ended combustion chamber supported therein for admitting pressurized air from within said housing to the upstream open end of said chamber for supporting primary combustion therein, said apparatus comprising: a fuel nozzle for discharging liquid fuel into said combustion chamber adjacent said upstream open end thereof; a collar member encircling said fuel nozzle generally adjacent the discharge end thereof in a spaced relationship providing an annular space therebetween, said member defining a plurality of individual radially directed passages for airflow communication from within said housing to said annular space, and an annular lip extending from said collar radially inwardly and in spaced relation to the nozzle face to direct air in said annular space across said nozzle face, a plurality of first passages extending axially through said collar in a helical configuration and having an inlet in said housing providing flow communication through said passages from within said housing to substantially adjacent the open end of said combustion chamber, and a plurality of second passages extending axially through said collar in a helical configuration from a separate confined cavity adjacent said nozzle to substantially adjacent the open end of said combustion chamber, said first and second passages imparting a codirectional helical discharge to fluid flowing therethrough; and, means downstream of the discharge of said first and second passages defining a plurality of individual generally tangentially directed air passages for airflow communication from within said housing to substantially adjacent the open end of said combustion chamber; whereby pressurized air from within said housing is directed into the open end of said combustion chamber as primary combustion air with a portion of said air entering through said first passages and having an axially swirling helical motion and another portion of said primary air having a tangentially swirling motion as directed by said tangential passages to provide confined mixing of said primary air with the fuel introduced by said nozzle, and a limited portion of air directed across said nozzle face to prevent carbon build-up thereon.

Claim 2

Dependent Claim 346 words

Combustion apparatus for a gas turbine engine having a housing enclosing a generally open-ended combustion chamber supported therein for admitting pressurized air from within said housing to the upstream open end of said chamber for supporting primary combustion therein, said apparatus comprising: a fuel nozzle for discharging liquid fuel into said combustion chamber adjacent said upstream open end thereof; a collar member encircling said fuel nozzle generally adjacent the discharge end thereof in a spaced relationship providing an annular space therebetween, said member defining a plurality of individual radially directed passages for airflow communication from within said housing to said annular space, and an annular lip extending from said collar radially inwardly and in spaced relation to the nozzle face to direct air in said annular space across said nozzle face, a plurality of first passages extending axially through said collar in a helical configuration and having an inlet in said housing providing flow communication through said passages from within said housing to substantially adjacent the open end of said combustion chamber, and a plurality of second passages extending axially through said collar in a helical configuration from a separate confined cavity adjacent said nozzle to substantially adjacent the open end of said combustion chamber, said first and second passages imparting a codirectional helical discharge to fluid flowing therethrough; and, means downstream of the discharge of said first and second passages defining a plurality of individual generally tangentially directed air passages for airflow communication from within said housing to substantially adjacent the open end of said combustion chamber; whereby pressurized air from within said housing is directed into the open end of said combustion chamber as primary combustion air with a portion of said air entering through said first passages and having an axially swirling helical motion and another portion of said primary air having a tangentially swirling motion as directed by said tangential passages to provide confined mixing of said primary air with the fuel introduced by said nozzle, and a limited portion of air directed across said nozzle face to prevent carbon build-up thereon.

Claim 3

Dependent Claim 23 words

Structure according to claim 1 wherein said second passages are alternatively connected to a fuel gas supply or a primary combustion air supply.

Claim 4

Dependent Claim 52 words

Structure according to claim 1 further including a first baffle member concentric with the wall defining the inlet to the combustion chamber and closely spaced therefrom, and openings in said wall to provide airflow into said space for a film of cooling air over said wall as directed by said baffle member.

Claim 5

Dependent Claim 80 words

Structure according to claim 3 wherein said means defining said tangential passages also supports a pair of closely spaced concentric baffle members with the radially outermost of said latter baffle members being in substantial alignment with said first baffle member and containing apertures for admitting airflow to the space between said latter baffle members for directing a film of cooling air across the face of said first baffle member as confined by the radially innermost of said latter baffle members.

Claim 6

Dependent Claim 329 words

In a gas turbine engine having a combustion chamber and a fuel nozzle disposed adjacent the open inlet end of said chamber for admitting liquid fuel therein for combustion within said chamber, means disposed adjacent the discharge end of said nozzle for confining the primary combustion air entering said open end of said chamber to a swirling motion to enhance complete mixture of the air and fuel prior to combustion, said means also including a plurality of passages for admitting gaseous fuel to said combustion chamber, said means comprising: a collar member encircling the nozzle adjacent the discharge end in an annular spaced relationship, said member defining an annular confined fuel gas cavity therein and a plurality of first and second passages extending through an axial extent of said member in an alternating arrangement and angularly disposed with respect to the axis, entry ports into said first passages for providing flow communication of primary combustion air therethrough from adjacent said nozzle to enter said combustion chamber in a generally helical swirl as directed by said first passages and said second passages providing flow communication from said confined fuel gas cavity to said combustion chamber and imparting a similar helical swirl to fluid flowing therethrough, said member further defining a plurality of generally radially extending passages for airflow communication to said annular space and an annular lip extending radially inwardly to overlie in spaced relationship a portion of the face of the nozzle to direct airflow in said annular space across said nozzle face; and, means defining tangentially extending passages disposed between the discharge of said first and second passages and the primary zone of the combustion chamber for airflow communication in a tangential swirl path to intercept the axial swirl path of fluid exiting the collar member to provide a generally confined mixing of said primary combustion air and said fuel injected by said nozzle in a generally helical swirl adjacent the open inlet end of said combustion chamber.

Claim 7

Dependent Claim 329 words

In a gas turbine engine having a combustion chamber and a fuel nozzle disposed adjacent the open inlet end of said chamber for admitting liquid fuel therein for combustion within said chamber, means disposed adjacent the discharge end of said nozzle for confining the primary combustion air entering said open end of said chamber to a swirling motion to enhance complete mixture of the air and fuel prior to combustion, said means also including a plurality of passages for admitting gaseous fuel to said combustion chamber, said means comprising: a collar member encircling the nozzle adjacent the discharge end in an annular spaced relationship, said member defining an annular confined fuel gas cavity therein and a plurality of first and second passages extending through an axial extent of said member in an alternating arrangement and angularly disposed with respect to the axis, entry ports into said first passages for providing flow communication of primary combustion air therethrough from adjacent said nozzle to enter said combustion chamber in a generally helical swirl as directed by said first passages and said second passages providing flow communication from said confined fuel gas cavity to said combustion chamber and imparting a similar helical swirl to fluid flowing therethrough, said member further defining a plurality of generally radially extending passages for airflow communication to said annular space and an annular lip extending radially inwardly to overlie in spaced relationship a portion of the face of the nozzle to direct airflow in said annular space across said nozzle face; and, means defining tangentially extending passages disposed between the discharge of said first and second passages and the primary zone of the combustion chamber for airflow communication in a tangential swirl path to intercept the axial swirl path of fluid exiting the collar member to provide a generally confined mixing of said primary combustion air and said fuel injected by said nozzle in a generally helical swirl adjacent the open inlet end of said combustion chamber.

Claim 8

Dependent Claim 32 words

Structure according to claim 5 wherein said confined fuel gas cavity is supplied with said primary combustion air whereby both first and second passages provide swirling combustion air into said combustion chamber.

Claim 9

Dependent Claim 52 words

Structure according to claim 5 further including a first baffle member concentric with the wall defining the inlet to the combustion chamber and closely spaced therefrom, and openings in said wall to provide airflow into said space for a film of cooling air over said wall as directed by said baffle member.

Claim 10

Dependent Claim 78 words

Structure according to claim 7 wherein said means defining said tangential passages also supports a pair of closely spaced concentric baffle members with the radially outermost of said latter baffle members being in substantial alignment with said first baffle member and containing apertures for admitting airflow to the space between said latter members for a film of cooling air across the face of said first baffle member as directed by the radially innermost of said latter baffle members.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1982-05-21	1982-11-20	1983-05-22	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1986-05-21	1986-11-20	1987-05-22	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1990-05-21	1990-11-20	1991-05-22	$7700.00	Window Closed / Lapsed

Combustion apparatus for a gas turbine engine

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