A robust, thermally and structurally sound burn pit flare tip structure is disclosed of refractory brick construction capable of resisting the high temperature of 1800° C. and associated fluctuations. The burn pit is capable of prolonged continuous operation and reduces the previously experienced downtime and frequent failures.

The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an internal annular wall and an external annular wall provided with air intake openings, the module further comprising an internal housing and an external housing. According to the invention, at least one of the internal and external housings has, on the surface thereof facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being produced facing one of the air intake openings in order to be visible from inside the combustion chamber and each indicating the angular position of a zone of the combustion chamber comprising the air intake opening.

The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an internal annular wall and an external annular wall provided with air intake openings, the module further comprising an internal housing and an external housing. According to the invention, at least one of the internal and external housings has, on the surface thereof facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being produced facing one of the air intake openings in order to be visible from inside the combustion chamber and each indicating the angular position of a zone of the combustion chamber comprising the air intake opening.

Techniques regarding the composition and/or structure of oven walls are provided. For example, one or more embodiments described herein can comprise an oven with a heat source configured to heat a hollow space within the oven. The oven further can comprise an oven body that can define the hollow space. Also, the oven body can comprising a plurality of connected sides, wherein one or more of the connected sides comprise a plurality of carbon nanotubes.

Techniques regarding the composition and/or structure of oven walls are provided. For example, one or more embodiments described herein can comprise an oven with a heat source configured to heat a hollow space within the oven. The oven further can comprise an oven body that can define the hollow space. Also, the oven body can comprising a plurality of connected sides, wherein one or more of the connected sides comprise a plurality of carbon nanotubes.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO.sub.2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO.sub.2 circulating fluid. Fuel derived CO.sub.2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO.sub.2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO.sub.2 circulating fluid. Fuel derived CO.sub.2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

An improved ceramic heat shield for a gas turbine is provided. The ceramic heat shield has a porous ceramic body and according to the embodiments an infiltration coating that is provided in a surface layer of the porous ceramic body and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body.

An improved ceramic heat shield for a gas turbine is provided. The ceramic heat shield has a porous ceramic body and according to the embodiments an infiltration coating that is provided in a surface layer of the porous ceramic body and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body.

A robust, thermally and structurally sound burn pit flare tip structure is disclosed of refractory brick construction capable of resisting the high temperature of 1800° C. and associated fluctuations. The burn pit is capable of prolonged continuous operation and reduces the previously experienced downtime and frequent failures.