43results about How to "Shorten flame length" patented technology

Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion. Despite this emissions advantage, catalytic combustion systems can increase the level of CO in the turbine exhaust. According to aspects of the invention, vortex formation devices includes vortex generators, swirlers and mixers can be placed downstream of each catalytic module surrounding the pilot nozzle so as to form one or more vortices in the otherwise substantially laminar flow exiting the modules. The vortices can create a suction so that a portion of the flow exiting the pilot nozzles is mixed with the flow exiting the catalyst modules. The introduction of the higher temperature pilot flow can accelerate the catalytic reaction time, promoting burnout of the CO formed during combustion.

A burner 1 for combustion chamber is provided with a cylindrical mixing portion 3 that mixes air for combustion (oxidizing agent) and fuel in the interior thereof and has one end 3a that opens to a combustion portion 2; a spray nozzle (fuel spraying portion) 5 that sprays fuel in the mixing portion 3, being disposed on another end 3b of the mixing portion 3; first blowing ports 6 that introduce the air for combustion to the mixing portion 3 to form a swirling flow with the fuel, being disposed to open to the inner wall of the mixing portion 3; and second blowing ports 7 that additionally introduce the air for combustion to the mixing portion 3, opening in a direction different from the first blowing ports 6 and being disposed further to the other end 3b side of the mixing portion 3 than the swirling flow. The burner for combustion chamber and combustion method of the present invention can shorten the flame length in the central axial direction by improving the combustion efficiency even during low loading and shorten the overall length of the burner for combustion chamber in the central axial direction.

An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

The invention discloses an afterburner integrated with a stabilizer and a worm wheel rear rectification support plate. A combustion part in the afterburner is integrated with a worm wheel rear load-bearing framework; the worm wheel rear rectification support plate is integrated with an inner culvert flame stabilizer, and cooling air is fed; a fuel oil supply pipe and a fuel oil nozzle are arranged in the rectification support plate; main fuel oil is transversely sprayed out from two sides of the support plate; and duty fuel oil is sprayed out from a groove on the rear surface of the stabilizer to form a duty flame. A pneumatic appearance of an outer culvert flame stabilizer is designed as a V-shaped bluff body, and the cooling air is fed into the outer culvert flame stabilizer; a fuel oil pipeline is arranged in the outer culvert flame stabilizer; the main fuel oil is transversely sprayed by a baffle plate nozzle; and the duty fuel oil is sprayed out from a groove on the rear surface of the outer culvert flame stabilizer. An annular flame stabilizer is arranged between the inner culvert flame stabilizer and the outer culvert flame stabilizer, so that functions of the stabilizer and a flame coupler are realized in a circumferential direction. The internal parts of the afterburner are integrated, so that the part utilization efficiency is improved, and the engine thrust-weight ratio is increased.

The invention provides a combustion chamber adopting a swirl vane tail edge pre-film atomization mode. The combustion chamber comprises a combustion chamber flame tube, a center level oil and gas mixing assembly and a main combustion level oil and gas mixing assembly which is arranged at the front end of the combustion chamber flame tube and the periphery of the center level oil and gas mixing assembly. The main combustion level oil and gas mixing assembly comprises a main combustion level swirl channel, N wedge-shaped swirl vanes and M vane interior oil paths; the N wedge-shaped swirl vanes are slantly fixed to the interior of the main combustion level swirl channel, and the M vane interior oil paths are arranged in at least one part of wedge-shaped swirl vanes respectively; the front end of each vane interior oil path is connected with a main combustion level oil cavity, and the tail end of the each vane interior oil path extends to the tail edge of the corresponding wedge-shaped swirl vane; the M is smaller than or equal to the N. The swirl vanes are wedge-shaped; velocity gradients are formed at the tail edges of the swirl vanes; a fuel liquid film flowing out of the tail edges of the swirl vanes is rapidly shorn and atomized under the action of the velocity gradients; the oil and gas blending distance is short, and the flame length and the length of the flame tube are shortened.

The invention aims to provide a dual-fuel swirling atomizing nozzle for chemical regenerative cycle, which comprises an outer swirler hub, a main oil way, a main cracked gas channel and swirler blades. An oil inlet is arranged on the outer swirler hub and communicated with the main oil way, the main oil way is communicated with oil spraying pores on windward sides of the swirler blades through branch channels of the oil way, and the main cracked gas channel is communicated with cracked gas nozzles on lee sides of the swirler blades through branch cracked gas channels. By the aid of the dual-fuel swirling atomizing nozzle, cracked gas fuels and air can be effectively mixed, flame is further shortened, and combustion efficiency and the integral performance of a gas turbine are improved. A swirler is combined with the nozzle, so that the head structure of a combustion chamber is more compact, and arrangement and installation of the combustion chamber are facilitated. Liquid fuels and the cracked gas fuels are independently supplied, so that the proportion of input fuels under various working conditions can be precisely controlled and mastered, and adaptability and economy of a combustion engine under the various working conditions are improved.

The invention aims at providing a cracking-gas fuel injection device for chemical regenerative cycle, comprising an inner hub, a middle hub, an outer hub, inner-stage swirl vanes, outer-stage swirl vanes and a center body cap hood, wherein the inner-stage swirl vanes are arranged between the inner hub and the middle hub; the outer-stage swirl vanes are arranged between the middle hub and the outer hub; a central through hole is arranged in the inner hub; a fuel feeding channel is formed between the inner hub and the central through hole and is closed by the center body cap hood; the inner hub is provided with an inlet channel of cracking gas fuel; the middle hub is provided with a cracking gas ring cavity; a spraying nozzle is arranged at the end part of the cracking gas ring cavity; a divergent channel is formed by the inner-stage swirl vanes and the outer-stage swirl vanes; and gas sprayed from the spraying nozzle enters a combustion chamber through the divergent channel. The cracking-gas fuel injection device provided by the invention has the advantages that the cracking gas fuel and air can be well mixed, so that the length of flame is further shortened, the length of the combustion chamber can be shortened, and further the structure of a gas turbine becomes compact.

The invention discloses a coal powder turbulent burner comprising a pre-burning chamber and a burner body. The burner body comprises a central air pipe, a primary air pipe and a secondary air pipe. The front end of the burner body extends into the pre-burning chamber. By arranging a truncated-cone-type blunt body diverging in the airflow direction at a primary air outlet of the primary air pipe, the mixing time of secondary air airflow of the secondary air pipe and coal powder airflow is prolonged, the length of a flame formed by burning of coal powder at an opening of the primary air pipe isdecreased, and low-nitrogen burning is facilitated; meanwhile, by arranging the truncated-cone-type blunt body, the secondary air airflow of the secondary air pipe forms a strong backflow area at a secondary air outlet, the burning temperature in the pre-burning chamber is decreased, and the coking phenomenon in the pre-burning chamber is effectively avoided; and the truncated-cone-type blunt bodyand the pre-burning chamber are matched in use, therefore, the truncated-cone-type blunt body can suck high-temperature flue gas in a furnace in a rolling mode, the anti-interference capability of the pre-burning can be improved during burning, and accordingly the steady burning performance of the coal powder is improved.

A torch burner of steam combustion-assisting type consists of cylinder body, central jet pipe of steam, steam ring pipe, nozzle and jet pipe of steam-air. It is featured as setting nozzle jacketed on steam ring pipe far from top of cylinder body, aligning nozzle to entrance of jet pipe of steam-air and setting steam jet component far from high temperature region at top of burner.