Variable geometry combustor apparatus

Claim 2

High performance variable geometry combustor apparatus, said apparatus having an axis and comprising: (a) wall means defining a combustion flow passage extending downstream from an upstream end wall portion of said wall means along and within a sidewall portion thereof, said sidewall portion having an inwardly projecting section positioned downstream from said end wall portion; (b) nozzle means, projecting inwardly through said sidewall portion generally opposite from said inwardly projecting section thereof, for injecting fuel into said flow passage, said nozzle means being spaced apart from said inwardly projecting sidewall section and cooperating therewith to define in said flow passage; (1) a pilot combustion zone adjacent said upstream end wall portion, (2) a main combustion zone positioned downstream from and communicating with said pilot zone, and (3) a barrier for sheltering combustion in said pilot combustion zone against back pressure in said flow passage or adverse interaction with combustion in said main combustion zone; and (c) means for flowing a selectively variable quantity of pressurized combustion air from a source thereof into said pilot combustion zone, said means (c) including a plurality of mutually spaced inlet openings extending through said end wall, a plurality of valve means each secured to said end wall over one of said openings therein, and means for simultaneously operating said valve means, said means for simultaneously operating said valve means comprising an actuating member rotatable relative to said wall means about said axis, and linking means interconnected between said actuating member and said valve means for simultaneously operating said valve means in response to rotation of said actuating member, said actuating member being a unison ring carried by said wall means for rotation about said axis, said valve means each having an actuating rod rotatable about an axis generally parallel to said apparatus axis, and said linking means being interconnected between said unison ring and said valve actuation rods to cause simultaneous rotation of said valve actuation rods in response to rotation of said unison ring.

Claim 3

High performance variable geometry combustor apparatus comprising: (a) wall means defining a combustion flow passage extending downstream from an upstream end wall portion of said wall means along and within a sidewall portion thereof, said sidewall portion having an inwardly projecting section positioned downstream from said end wall portion; (b) nozzle means, projecting inwardly through said sidewall portion generally opposite from said inwardly projecting section thereof, for injecting fuel into said flow passage, said nozzle means being spaced apart from said inwardly projecting sidewall section and cooperating therewith to define in said flow passage: (1) a pilot combustion zone adjacent said upstream end wall portion, (2) a main combustion zone positioned downstream from and communicating with said pilot combustion zone, and (3) a barrier for sheltering combustion in said pilot combustion zone against back pressure in said flow passage or adverse interaction with combustion in said main combustion zone; and (c) means for flowing a selectively variable quantity of pressurized combustion air from a source thereof into said pilot combustion zone, said nozzle means (b) including means for selectively injecting fuel into either or both of said pilot and main combustion zones.

Claim 4

High performance variable geometry combustor apparatus comprising: (a) wall means defining a combustion flow passage extending downstream from an upstream end wall portion of said wall means along and within a sidewall portion thereof, said sidewall portion having an inwardly projecting section positioned downstream from said end wall portion; (b) nozzle means, projecting inwardly through said sidewall portion generally opposite from said inwardly projecting section thereof, for injecting fuel into said flow passage, said nozzle means being spaced apart from said inwardly projecting sidewall section and cooperating therewith to define in said flow passage: (1) a pilot combustion zone adjacent said upstream end wall portion, (2) a main combustion zone positioned downstream from and communicating with said pilot combustion zone, and (3) a barrier for sheltering combustion in said pilot combustion zone against back pressure in said flow passage or adverse interaction with combustion in said main combustion zone; and (c) means for flowing a selectively variable quantity of pressurized combustion air from a source thereof into said pilot combustion zone, said nozzle means (b) including means for selectively injecting fuel into either or both of said pilot and main combustion zones.

Claim 5

A variable geometry gas turbine engine combustor comprising: (a) a liner having an upstream end wall, a sidewall portion extending from said end wall and defining therewith a combustion flow passage, said sidewall portion having an inwardly projecting section positioned downstream from said end wall; (b) a housing receiving said end wall and said sidewall portion and defining therewith a plenum for receiving pressurized air from a source thereof; (c) fuel nozzle means projecting into said flow passage through said sidewall portion at a location generally opposite said inwardly projecting section thereof, said fuel nozzle means being spaced apart from said inwardly projecting sidewall section and cooperating therewith to define in said flow passage a pilot combustion zone positioned between said sidewall section and said end wall, and a main combustion zone communicating with said pilot combustion zone and positioned downstream from said sidewall section, said fuel nozzle means being operable to selectively inject fuel into either or both of said pilot and main combustion zone; and (d) means for admitting a selectively variable quantity of pressurized air from said plenum into said pilot combustion zone, wherein said end wall is of an annular configuration and circumscribes an axis of said combustor, said sidewall portion includes annular, mutually spaced radially inner and outer sidewalls extending in a downstream direction from said end wall, and wherein said means (d) include a circumferentially spaced series of inlet openings extending through said end wall, a circumferentially spaced series of inlet valves each operatively connected to said end wall over one of said inlet openings, and means for simultaneously operating said inlet valves, said inlet valves having rotatable actuating rods, and said means for simultaneously operating said inlet valves including an actuating ring positioned in said plenum, means for supporting said ring from said liner for rotation about said axis, linking means interconnected between said ring and said rods for simultaneously rotating said rods in response to rotation of said ring, and means for selectively rotating said ring.

Claim 6

A variable geometry gas turbine engine combustor comprising: (a) a liner having an upstream end wall, a sidewall portion extending from said end wall and defining therewith a combustion flow passage, said sidewall portion having an inwardly projecting section positioned downstream from said end wall; (b) a housing receiving said end wall and said sidewall portion and defining therewith a plenum for receiving pressurized air from a source thereof; (c) fuel nozzle means projecting into said flow passage through said sidewall portion at a location generally opposite said inwardly projecting section thereof, said fuel nozzle means being spaced apart from said inwardly projecting sidewall section and cooperating therewith to define in said flow passage a pilot combustion zone positioned between said sidewall section and said end wall, and a main combustion zone communicating with said pilot combustion zone and positioned downstream from said sidewall section, said fuel nozzle means being operable to selectively inject fuel into either or both of said pilot and main combustion zone; and (d) means for admitting a selectively variable quantity of pressurized air from said plenum into said pilot combustion zone, wherein said end wall is of an annular configuration and circumscribes an axis of said combustor, said sidewall portion includes annular, mutually spaced radially inner and outer sidewalls extending in a downstream direction from said end wall, and wherein said means (d) include a circumferentially spaced series of inlet openings extending through said end wall, a circumferentially spaced series of inlet valves each operatively connected to said end wall over one of said inlet openings, and means for simultaneously operating said inlet valves, said inlet valves having rotatable actuating rods, and said means for simultaneously operating said inlet valves including an actuating ring positioned in said plenum, means for supporting said ring from said liner for rotation about said axis, linking means interconnected between said ring and said rods for simultaneously rotating said rods in response to rotation of said ring, and means for selectively rotating said ring.

Claim 7

The combustor of claim 3 wherein said means for selectively rotating said actuating ring comprise a control member connected to said ring, extending outwardly through said housing, and movable relative to said housing along an axis generally perpendicular to said combustor axis to selectively rotate said actuating ring.

Claim 8

A variable geometry combustor for a gas turbine propulsion engine or the like, comprising: (a) a hollow, annular combustor liner having an annular upstream end wall from which mutually spaced radially inner and outer sidewalls extend in a downstream direction, said liner end wall having a circumferentially spaced series of air inlet openings extending axially therethrough, said walls of said liner defining in said combustor a combustion flow passage, a portion of said radially inner sidewall projecting into said combustion flow passage and partially dividing the same into a pilot combustion zone portion adjacent said end wall, and a main combustion zone positioned downstream from said pilot combustion zone portion; (b) a hollow, annular combustor housing coaxially enveloping an upstream end portion of said liner and defining therewith an intake plenum for receiving pressurized air from a source thereof, said housing having an end wall axially spaced in an upstream direction from said liner end wall; (c) a circumferentially spaced series of valve means each secured to said liner end wall at one of said inlet openings therein and operable to flow a selectively variable quantity of pressurized air from said plenum into the liner interior through such opening; and (d) means for simultaneously operating each of said valve means, said means (d) comprising a series of actuating rods each rotatably connected to one of said valve means to operate the same, a unison ring, means for coaxially mounting said unison ring within said intake plenum for rotation relative to said liner, means for selectively rotating said unison ring, and means interconnected between said unison ring and said actuating rods for rotating said rods in response to rotation of said unison ring, (e) means for imparting a swirling flow pattern to air entering the liner interior through said inlet openings in said liner end wall; and (f) a circumferentially spaced series of nozzle means each projecting generally radially into the liner interior through said radially outer sidewall at a location spaced in a downstream direction from said liner end wall end radially opposite said projecting radially inner sidewall portion, said nozzle means each being operable to inject fuel into a selected one or both of said pilot and main combustion zones of said flow passage, and being spaced apart from said inwardly projecting portion of said radially inner sidewall.

Claim 9

A variable geometry combustor for a gas turbine propulsion engine or the like, comprising: (a) a hollow, annular combustor liner having an annular upstream end wall from which mutually spaced radially inner and outer sidewalls extend in a downstream direction, said liner end wall having a circumferentially spaced series of air inlet openings extending axially therethrough, said walls of said liner defining in said combustor a combustion flow passage, a portion of said radially inner sidewall projecting into said combustion flow passage and partially dividing the same into a pilot combustion zone portion adjacent said end wall, and a main combustion zone positioned downstream from said pilot combustion zone portion; (b) a hollow, annular combustor housing coaxially enveloping an upstream end portion of said liner and defining therewith an intake plenum for receiving pressurized air from a source thereof, said housing having an end wall axially spaced in an upstream direction from said liner end wall; (c) a circumferentially spaced series of valve means each secured to said liner end wall at one of said inlet openings therein and operable to flow a selectively variable quantity of pressurized air from said plenum into the liner interior through such opening; and (d) means for simultaneously operating each of said valve means, said means (d) comprising a series of actuating rods each rotatably connected to one of said valve means to operate the same, a unison ring, means for coaxially mounting said unison ring within said intake plenum for rotation relative to said liner, means for selectively rotating said unison ring, and means interconnected between said unison ring and said actuating rods for rotating said rods in response to rotation of said unison ring, (e) means for imparting a swirling flow pattern to air entering the liner interior through said inlet openings in said liner end wall; and (f) a circumferentially spaced series of nozzle means each projecting generally radially into the liner interior through said radially outer sidewall at a location spaced in a downstream direction from said liner end wall end radially opposite said projecting radially inner sidewall portion, said nozzle means each being operable to inject fuel into a selected one or both of said pilot and main combustion zones of said flow passage, and being spaced apart from said inwardly projecting portion of said radially inner sidewall.