A gas turbine engine includes: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and include a combustor mean radius; and a turbine section fluidly coupled downstream of the combustor section and a turbine mid-span radius. The combustor mean radius is greater than each of the compressor mean radius and the turbine mid-span radius.

A gas turbine engine includes: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and include a combustor mean radius; and a turbine section fluidly coupled downstream of the combustor section and a turbine mid-span radius. The combustor mean radius is greater than each of the compressor mean radius and the turbine mid-span radius.

A gas turbine engine includes: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and include a combustor mean radius; and a turbine section fluidly coupled downstream of the combustor section and a turbine mid-span radius. The combustor mean radius is greater than each of the compressor mean radius and the turbine mid-span radius.

A swirl mesh lean direct injection concept for distributed flame holding for low pollutant emissions and mitigation of combustion instability. The invention further relates to a new method for flame holding with least pressure drop and flame temperature, in gas turbine engine combustors, wherein the liner of the combustor is partially or fully replaced with a “swirl mesh”. The invention has lean direct injection for fuel distribution over several points in gas turbine combustors along with swirl arrangement for air injection which provides low pollutant emission and low combustion instability.

A swirl mesh lean direct injection concept for distributed flame holding for low pollutant emissions and mitigation of combustion instability. The invention further relates to a new method for flame holding with least pressure drop and flame temperature, in gas turbine engine combustors, wherein the liner of the combustor is partially or fully replaced with a “swirl mesh”. The invention has lean direct injection for fuel distribution over several points in gas turbine combustors along with swirl arrangement for air injection which provides low pollutant emission and low combustion instability.

An integrated process for producing acetylene is provided. The process comprises separating a gas stream comprising methane from a fuel gas stream in a fuel gas recovery unit of a process. A fuel and an oxidizer are combusted in a combustion zone of a pyrolytic reactor to create a combustion gas stream, wherein the pyrolytic reactor is integrated with the fuel gas recovery unit via the gas stream comprising methane. A light hydrocarbon stream comprising all or a first portion of the gas stream comprising methane is injected into a supersonic combustion gas stream to create a mixed stream. The velocity of the mixed stream is transitioned from supersonic to subsonic in a reaction zone of the pyrolytic reactor to produce a reaction mixture comprising acetylene, methane, carbon oxides, and hydrogen. The reaction mixture is separated to provide an acetylene stream.

An integrated process for producing acetylene is provided. The process comprises separating a gas stream comprising methane from a fuel gas stream in a fuel gas recovery unit of a process. A fuel and an oxidizer are combusted in a combustion zone of a pyrolytic reactor to create a combustion gas stream, wherein the pyrolytic reactor is integrated with the fuel gas recovery unit via the gas stream comprising methane. A light hydrocarbon stream comprising all or a first portion of the gas stream comprising methane is injected into a supersonic combustion gas stream to create a mixed stream. The velocity of the mixed stream is transitioned from supersonic to subsonic in a reaction zone of the pyrolytic reactor to produce a reaction mixture comprising acetylene, methane, carbon oxides, and hydrogen. The reaction mixture is separated to provide an acetylene stream.

A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow.

A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow.

A fuel injection system includes an outer support defining a fuel manifold and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extending in an axial direction from the feed arm for feeding respective injection nozzles. The feed arm defines a plurality of fuel passages therethrough in fluid communication with the fuel manifold and outlet openings to supply fuel from the fuel manifold to the outlet openings. A heat shield extends from the outer support to the inner support and extends about the outer support and the feed arm to provide heat shielding to the fuel manifold and the fuel passages.