Abstract: A pressure reduction system and methods therefore that include features for reducing the pressure of a high pressure aerosol to ambient pressure without significantly changing the characteristics of the aerosol are provided. In this manner, the non-volatile particulate matter concentration in a sample stream obtained from the aerosol stream at ambient pressure is representative of the non-volatile particulate matter concentration that was present in the aerosol stream at high pressure prior to the pressure reduction.

Abstract: A pressure reduction system and methods therefore that include features for reducing the pressure of a high pressure aerosol to ambient pressure without significantly changing the characteristics of the aerosol are provided. In this manner, the non-volatile particulate matter concentration in a sample stream obtained from the aerosol stream at ambient pressure is representative of the non-volatile particulate matter concentration that was present in the aerosol stream at high pressure prior to the pressure reduction.

Abstract: A pressure reduction system and methods therefore that include features for reducing the pressure of a high pressure aerosol to ambient pressure without significantly changing the characteristics of the aerosol are provided. In this manner, the non-volatile particulate matter concentration in a sample stream obtained from the aerosol stream at ambient pressure is representative of the non-volatile particulate matter concentration that was present in the aerosol stream at high pressure prior to the pressure reduction.

Abstract: A pressure reduction system and methods therefore that include features for reducing the pressure of a high pressure aerosol to ambient pressure without significantly changing the characteristics of the aerosol are provided. In this manner, the non-volatile particulate matter concentration in a sample stream obtained from the aerosol stream at ambient pressure is representative of the non-volatile particulate matter concentration that was present in the aerosol stream at high pressure prior to the pressure reduction.

Abstract: A gas turbine engine augmentor includes an inter-liner cavity including an axially extending annular gap separating augmentor and tailpipe liners. A purge flow cavity is in fluid communication with a fan bypass duct and with the cavity. An ejector in fluid communication with the bypass duct includes an ejector nozzle positioned and aimed to direct an ejector nozzle flow from inside the ejector nozzle across the cavity. The purge flow cavity may be bifurcated into forward and aft purge flow cavities which are in fluid communication with the ejector and inter-liner cavity respectively. An annular dividing wall having ejector metering apertures may be disposed between the forward purge flow cavity and an ejector plenum of the ejector. An annular trapped vortex cavity pilot may be located upstream of the annular gap. The aft purge flow cavity may be outwardly bounded by a seal having purge metering apertures disposed therethrough.

Abstract: A gas turbine engine augmentor includes an inter-liner cavity including an axially extending annular gap separating augmentor and tailpipe liners. A purge flow cavity is in fluid communication with a fan bypass duct and with the cavity. An ejector in fluid communication with the bypass duct includes an ejector nozzle positioned and aimed to direct an ejector nozzle flow from inside the ejector nozzle across the cavity. The purge flow cavity may be bifurcated into forward and aft purge flow cavities which are in fluid communication with the ejector and inter-liner cavity respectively. An annular dividing wall having ejector metering apertures may be disposed between the forward purge flow cavity and an ejector plenum of the ejector. An annular trapped vortex cavity pilot may be located upstream of the annular gap. The aft purge flow cavity may be outwardly bounded by a seal having purge metering apertures disposed therethrough.

Abstract: A gas turbine engine augmentor includes an annular trapped vortex cavity pilot having a cavity forward wall, a cavity radially outer wall, and a cavity aft wall, an annular cavity therebetween, and cavity fuel injector tubes operably disposed through the outer wall into the cavity. Circumferentially spaced apart radial flameholders with integral spraybars and/or radial spraybars interdigitated with the radial flameholders radially inwardly into an exhaust flowpath of the augmentor just forward and upstream of the trapped vortex cavity pilot at a radially outer portion of a combustion zone of the exhaust flowpath. An annular trapped dual vortex cavity pilot version is operable for producing trapped dual counter-rotating inner and outer vortices of fuel and air mixtures.

Abstract: A gas turbine engine augmentor includes an annular trapped vortex cavity pilot having a cavity forward wall, a cavity radially outer wall, and a cavity aft wall, an annular cavity therebetween, and cavity fuel injector tubes operably disposed through the outer wall into the cavity. Circumferentially spaced apart radial flameholders with integral spraybars and/or radial spraybars interdigitated with the radial flameholders radially inwardly into an exhaust flowpath of the augmentor just forward and upstream of the trapped vortex cavity pilot at a radially outer portion of a combustion zone of the exhaust flowpath. An annular trapped dual vortex cavity pilot version is operable for producing trapped dual counter-rotating inner and outer vortices of fuel and air mixtures.