A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.

A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.

A combustion tube for a gas turbine including an outlet section having a cross-section of an annular sector-shape. The outlet section includes an outer wall forming an outer peripheral boundary of the annular sector-shape, an inner wall forming an inner peripheral boundary of the annular sector-shape, and a pair of side walls forming boundaries on both sides of the annular sector-shape in a circumferential direction, respectively. The outer wall extends obliquely with respect to the inner wall such that a height of the annular sector-shape decreases toward an outlet opening of the combustion tube. A first side wall extends obliquely with respect to a second side such that a perimeter of the annular sector-shape increases toward the outlet opening of the combustion tube. An inclination angle θ.sub.1 of the first side wall with respect to the second side wall satisfies 0<θ.sub.1≤56.

A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the lean burn fuel injector head tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction for a length and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, wherein the combustor chamber includes primary and secondary combustion zones. A ratio of the combustor chamber length to the lean burn fuel injector head tip diameter is less than 5.

A swirler assembly includes a primary swirler having a primary swirler connecting portion, a fuel nozzle connecting portion for connecting a fuel nozzle to the primary swirler, and a primary oxidizer flow passage that extends at least partially in the longitudinal direction, and a secondary swirler having a secondary swirler connecting member, where the primary swirler connecting portion and the secondary swirler connecting member engage to connect the primary swirler and the secondary swirler in the longitudinal direction, and to permit radial movement of the primary swirler with respect to the secondary swirler.

A swirler assembly includes a primary swirler having a primary swirler connecting portion, a fuel nozzle connecting portion for connecting a fuel nozzle to the primary swirler, and a primary oxidizer flow passage that extends at least partially in the longitudinal direction, and a secondary swirler having a secondary swirler connecting member, where the primary swirler connecting portion and the secondary swirler connecting member engage to connect the primary swirler and the secondary swirler in the longitudinal direction, and to permit radial movement of the primary swirler with respect to the secondary swirler.

The present invention is a turbofan propulsion system, based on a tangential gas turbine that is structurally a part of the propulsion system's centrifugal compressor, wherein the gas turbine's combustion chambers with nozzles are placed to rotate around a larger radius circle at a supersonic circumferential speed, and the fan blades are placed to rotate around a smaller radius circle at a subsonic circumferential speed, therefore increasing the efficiency of the propulsion system.

A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

A system for improving fuel-air mixing inside an injection system of a turbomachine combustion chamber. An air intake ring has an annular deflection wall, or venturi, having an internal profile provided with a discontinuity inducing an increase in the radius (φ) of the internal profile downstream of the discontinuity. A method of atomizing fuel includes separating fuel trickling over the internal profile of the annular deflection wall from the internal profile at the level of the discontinuity so as to form droplets within a flow of air coming from an upstream air circulation space of the air intake ring.

A system for improving fuel-air mixing inside an injection system of a turbomachine combustion chamber. An air intake ring has an annular deflection wall, or venturi, having an internal profile provided with a discontinuity inducing an increase in the radius (φ) of the internal profile downstream of the discontinuity. A method of atomizing fuel includes separating fuel trickling over the internal profile of the annular deflection wall from the internal profile at the level of the discontinuity so as to form droplets within a flow of air coming from an upstream air circulation space of the air intake ring.