An augmentor liner (10) is provided that includes an annulus (22) disposed between a first wall (18) and a second wall (20), and a plurality of baffles (34). The first wall (18) is disposed radially inside of the second wall (20). The plurality of baffles (34) extend heightwise between the first wall (18) and the second wall (20), and are circumferentially spaced apart from one another by a distance (40). The distance (40) between adjacent baffles (34) is such that an acoustic wave (42) entering an annulus compartment will travel between the first wall (18) and second wall (20) in a direction having a radial component that is substantially greater than a circumferential component. The baffle spacing (40) may alternatively be described as being such that the circumferential component of the acoustic wave is substantially damped and therefore does not materially contribute to undesirable screech.

A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

A method for fabricating an augmentor (100) includes fabricating an outer casing having at least one channel (133) defined therein, fabricating a centerbody (103) having at least one channel (134) defined therein, fabricating a plurality of turbine frame vanes (104), wherein each turbine frame vane includes a first sidewall having a first channel (126) defined therein, a second sidewall having a second channel (128) defined therein, and at least one cross-fire tube extending between the first sidewall and the second sidewall, and coupling the plurality of turbine frame vanes to the augmentor outer casing and to the centerbody such that the first sidewall first channel formed on a first turbine frame vane, the second sidewall second channel formed on a second turbine frame vane, the augmentor channel, and the centerbody channel define a substantially contiguous trapped vortex chamber (160).

A heat shield for protecting a fuel injection tube of a turbine engine afterburner. The heat shield includes a base (28) adapted for attachment to a duct member, the base having a first mounting surface (86), a first fastener hole (88), and a recess (90) in the base. A housing (30) encloses the fuel injection tube. The housing (30) has an internal channel (106) for receiving the fuel injection tube, a second mounting surface (100), a second fastener hole (102), and a tab (92) protruding from the housing. The tab (92) is sized and shaped for being received in the recess (90) of the base (28). The housing (30) may be secured to the base (28) at a mounting position wherein the tab (92) is received in the recess (90), the mounting surfaces (86, 100) are engaged, and the second fastener hole (102) is positioned in registration with the first fastener hole (88).

A turbofan gas turbine engine augmenter includes a fuel/air swirler (64) disposed between an axially extending bypass flowpath (25) and an axially extending exhaust flowpath (128). A swirler inlet (66) is axially open to and positioned substantially normal to the bypass flowpath (25) and a swirler outlet (68) is open to and positioned substantially parallel to the exhaust flowpath (128). A swirl chamber (67) within the fuel/air swirler (64) is between the swirler inlet (66) and the swirler outlet (68). A swirl axis (70) of the fuel/air swirler (64) extends through the swirler outlet (68) substantially normal to the exhaust flowpath (128). An air swirler (72) may be centered about the swirl axis (70) within the fuel/air swirler (64). The air swirler (72) may be a louvered or have a plurality of swirling vanes (78). The swirler inlet (66) may be radially offset with respect to the swirl axis (70). An air scoop (80) may lead from the swirler inlet (66) to a rounded swirler housing within which the air swirler (72) is disposed.