Combustion chamber wall

FIELD: machine building.

SUBSTANCE: turbomachine combustion chamber annular wall comprises cold side and hot side and has, at least, one primary hole to enable possibility of first air flow ingress, passing on wall cold side, to wall hot side for providing fuel combustion inside combustion chamber and plurality of cooling holes. Each cooling hole has diameter of not more than 1 mm in order to enable possibility of second flow of air ingress, passing on wall cold side, to wall hot side for wall hot side cooling. Plurality of cooling holes is also suitable for dilution of combustion gas, which is result of said combustion, due to use of air flow ingression on wall hot side through cooling holes. Said cooling holes represent not less than 50 % of entire surface area for air passage through wall.

EFFECT: invention is aimed for provision of more uniform temperature distribution inside combustion chamber at simultaneous increase of turbomachine hydro-dynamic cycle efficiency.

9 cl, 5 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine combustion chamber extends in circle relative to lengthwise axis A and is defined by outer lateral wall, inner lateral wall and circular chamber end wall connecting one end of outer lateral wall with one end of inner lateral wall. Outer lateral wall comprises spark plug distributed in its circumference, primary holes and dilution holes located downstream of primary holes in direction of lengthwise axis A. Primary holes located in every adjacent zone abutting on one of spark plugs are located downstream of primary holes located in said zones.

EFFECT: re-ignition at high altitude.

9 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: annular combustion chamber (10) of turbomachine, such as aircraft turbo-jet or turboprop engine, contains coaxial walls (14, 16) in the form of rotation bodies located one inside the other with holes (66) for primary air inlet and holes (66) for mixing air inlet into the chamber. Holes for primary air inlet and holes for mixing air inlet of each wall are actually aligned with each other along the chamber longitudinal axis (34) and form a single annular set of holes (66). The chamber contains the chamber bottom (18) wall joining inlet edges of its walls (14, 16) in the form of rotation bodies and containing holes (30), in which fuel injection systems (36) and deflectors (70) are installed. The distance (L) between annular set of holes (66) and the deflector measured along the hole axis (38) is in essence equal to half of height (H) of combustion primary zone in the chamber.

EFFECT: reducing release of nitrogen oxides from turbomachine combustion chamber using simple, effective and economic method.

12 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine combustion chamber wall includes at least one peripheral row of primary holes, at least one peripheral row of liquefaction holes and microperforation holes. All primary holes are located in one and the same axial position. Primary holes and liquefaction holes are uniformly distributed on the wall periphery. Liquefaction holes are divided at least in two different groups depending on the value of their diameter. Some part of liquefaction holes has maximum diameter, and the other part has minimum diameter. Multiperforation holes have diameters, which are smaller than minimum diameter of liquefaction holes. Liquefaction holes having maximum diameter and liquefaction holes having minimum diameter are equipped with a rear edge in the flow direction. Multiperforation holes are equipped with a front edge in the flow direction. Liquefaction holes having minimum diameter are offset in axial direction to the side of the flow movement in relation to liquefaction holes having maximum diameter. Rear edge of liquefaction holes of small diameter in the flow direction is located in one line in a circumferential direction with a rear edge of liquefaction holes in the flow direction, which have maximum diameter.

EFFECT: optimisation of arrangement of liquefaction holes; excluding the possibility of occurrence of random hot points, without increasing the quantity of polluting emissions.

5 cl, 6 dwg

FIELD: power engineering.

SUBSTANCE: turbomachine combustion chamber comprises an axis of gases flow, inner and outer circular walls, joined to each other by the chamber bottom. The inner and outer walls are accordingly equipped with at least one circumferential row of primary holes and at least one circumferential row of dissolution holes. Primary holes and dissolution holes are evenly distributed on the circumference of the inner and outer walls. All primary holes of the inner wall are arranged at one and the same axial distance (D) relative to the chamber bottom. All primary holes of the outer wall are arranged at one and the same axial distance relative to the chamber bottom. At least on one of inner or outer walls dissolution holes are distributed in the first row and in at least one second row. All dissolution holes of the first row are arranged at one and the same distance along the axis (Y) of the chamber relative to primary holes of the inner or outer wall. Primary holes are arranged in the same angular position as at least some dissolution holes of the second row, and position of dissolution holes of the first and second row arranged at the angle between two serially arranged primary holes forms a pattern that repeats along the entire circumference of the considered inner or outer wall.

EFFECT: elimination of aerodynamic relation of air jets outgoing from holes of two different types, without increase of quantity of pollutant emissions, without development of negative effect at temperature distribution at the outlet from the combustion chamber, thus optimising possibilities of repeated ignition.

17 cl, 9 dwg

Combustion chamber // 2470227

FIELD: heating.

SUBSTANCE: combustion chamber includes internal housing with sliding surface and external housing with sliding section of the wall and at least one cooling hole in the sliding section of the wall. Sliding surface and sliding section of the wall are attached to each other with possibility of sliding. Cooling hole is at least partially located in the sliding section of the wall so that it opens due to sliding movement of sliding surface in relation to sliding section of the wall when internal housing is thermally expanded, and/or closed due to sliding movement of sliding surface relative to sliding section of the wall when internal housing is thermally converged.

EFFECT: improvement of combustion chamber cooling.

7 cl, 7 dwg

FIELD: power engineering.

SUBSTANCE: tubular combustion chamber comprises a mostly cylindrical jacket comprising an inner cavity, an axis and a closed end of the axis. The closed end of the axis comprises a facility to inject fuel into the inner cavity of the jacket and an impact cooling sleeve. A mostly cylindrical insert of the combustion chamber is arranged coaxially inside the jacket and is arranged so that in combination with the jacket it makes it possible to set the borders of appropriate radially external channels for flowing air for combustion and dissolving air and appropriate radially internal cavities for the combustion area and dissolution area. The combustion area is located in direction of the axis at the side of the closed end of the jacket. The dissolution area is distanced in direction of the axis from the closed end of the jacket. The impact cooling sleeve is placed coaxially between the jacket and the combustion chamber insert and stretches in direction of the axis from the closed end of the jacket practically along the entire length of the combustion zone to the closed end of the sleeve. The sleeve is equipped with a large number of holes, which have the specified size and are distributed so that they make it possible to send air for combustion to the radially external surface of the combustion chamber insert section setting the combustion zone borders, for impact cooling. The radially external surface of the insert with impact cooling is made without holes. The flow of air for combustion and dissolving air passes in radially external channels in general in direction of the axis to the closed end of the jacket. The channel for dissolving air includes a large number of dissolution ports in the combustion chamber insert to ensure arrival of the dissolving air along the radius into the dissolution zone. The combustion chamber insert and the closed end of the axis are made so that actually the entire air for combustion before it arrives into the combustion zone flows through impact cooling holes.

EFFECT: invention provides for even distribution of flow sent to swirler blades, for operation with low emission of NOx and even pre-mixing with the help of swirler blades and more efficient ratio between fuel and air for the required NOx.

8 cl, 2 dwg

FIELD: power engineering.

SUBSTANCE: at least one of many mixing holes is a mixing hole, dimensions and location of which interfere with penetration of a liquid medium flow into the primary mixing zone located in the head end of the combustion chamber. During realisation of the method for improvement of fuel and air mixture homogeneity in a combustion chamber, obstacles are created on the way of the liquid medium flow penetration from at least one of may mixing holes into a fuel flow and the primary mixing zone of the combustion chamber head end. Liquid medium flow penetrates by at least 100%, but not by more than 165%, into the primary mixing zone. The liquid medium flow penetrating by more than 100% passes radially outside from the central body of the combustion chamber towards a cartridge. Multiple mixing holes are limited with a cartridge made in the combustion chamber, and interference is developed by giving specified diametre to multiple mixing holes and arrangement of many mixing holes along the cartridge in at least one of specified positions and in the specified quantity.

EFFECT: improved homogeneity of fuel and air mixture in a combustion chamber.

11 cl, 18 dwg

FIELD: machine building.

SUBSTANCE: in wall there are made multitude of primary orifices, multitude of orifices of dilution to ensure penetration of air moving from cold side of wall to hot side and ensuring combustion and dilution of fuel mixture with air and multitude of cooling orifices designed for penetration of air moving from cold side of wall to its hot side to generate film of cooling air along said wall. The primary orifices and dilution orifices are distributed along radial rows. The cooling orifices are distributed along multitude of radial rows spaced one from another in axial direction at a certain distance; number of these cooling orifices is equal in each of the said rows. A circular wall additionally has multitude of orifices of perforation arranged directly behind and downstream from the primary orifices and dilution orifices and distributed along multitude of circular rows. The perforation orifices of the same row have in essence equal diametre, are spaced from each other at a certain constant interval and possess characteristics different from corresponding characteristics of the said orifices of cooling in adjacent rows.

EFFECT: reduced cost and time for fabrication of circular wall of combustion chamber.

6 cl, 3 dwg

Gas turbine engine // 2382892

FIELD: engines and pumps.

SUBSTANCE: proposed gas turbine engine features turbine first-stage nozzle vanes arranged on combustion chamber gas collector outlet. Gas collector inner wall rear part is perforated and arranged on first-stage nozzle vane outer part. Its is limited by front and rear circular grooves arranged to receive nozzle vane radial ledges. U-like section compensator is arranged between perforated wall and read circular groove. Perforated wall outer surface is made equidistant from cooled surface of first-stage nozzle vane lower shelf.

EFFECT: higher reliability.

2 dwg

FIELD: combustion apparatus and combustion processes.

SUBSTANCE: heat protection shield comprises inner and outer sides and a group of individual passages for cooling gas whose inlets lie at the outer side and inlets lie at the inner side.

EFFECT: improved heat protection.

15 cl, 5 dwg

FIELD: gas-turbine engine engineering.

SUBSTANCE: flame tube comprises shell and at least one unit for supplying coolant made of openings arranged in the peripheral direction in the shell. The unit for supplying coolant is additionally provided with the grooves connected with the openings. The grooves are made in the inner side of the shell in the peripheral direction at a distance one from the other . The distance ranges from 0.5h to 3h, depth L of each groove ranges from 3h to 15h, and width S of each groove ranges from 2h to 15h, where h is the height of the groove.

EFFECT: enhanced reliability.

1 cl, 3 dwg

FIELD: combustion apparatus and combustion processes.

SUBSTANCE: heat protection shield comprises inner and outer sides and a group of individual passages for cooling gas whose inlets lie at the outer side and inlets lie at the inner side.

EFFECT: improved heat protection.

15 cl, 5 dwg

Gas turbine engine // 2382892

FIELD: engines and pumps.

SUBSTANCE: proposed gas turbine engine features turbine first-stage nozzle vanes arranged on combustion chamber gas collector outlet. Gas collector inner wall rear part is perforated and arranged on first-stage nozzle vane outer part. Its is limited by front and rear circular grooves arranged to receive nozzle vane radial ledges. U-like section compensator is arranged between perforated wall and read circular groove. Perforated wall outer surface is made equidistant from cooled surface of first-stage nozzle vane lower shelf.

EFFECT: higher reliability.

2 dwg

FIELD: machine building.

SUBSTANCE: in wall there are made multitude of primary orifices, multitude of orifices of dilution to ensure penetration of air moving from cold side of wall to hot side and ensuring combustion and dilution of fuel mixture with air and multitude of cooling orifices designed for penetration of air moving from cold side of wall to its hot side to generate film of cooling air along said wall. The primary orifices and dilution orifices are distributed along radial rows. The cooling orifices are distributed along multitude of radial rows spaced one from another in axial direction at a certain distance; number of these cooling orifices is equal in each of the said rows. A circular wall additionally has multitude of orifices of perforation arranged directly behind and downstream from the primary orifices and dilution orifices and distributed along multitude of circular rows. The perforation orifices of the same row have in essence equal diametre, are spaced from each other at a certain constant interval and possess characteristics different from corresponding characteristics of the said orifices of cooling in adjacent rows.

EFFECT: reduced cost and time for fabrication of circular wall of combustion chamber.

6 cl, 3 dwg

FIELD: power engineering.

SUBSTANCE: at least one of many mixing holes is a mixing hole, dimensions and location of which interfere with penetration of a liquid medium flow into the primary mixing zone located in the head end of the combustion chamber. During realisation of the method for improvement of fuel and air mixture homogeneity in a combustion chamber, obstacles are created on the way of the liquid medium flow penetration from at least one of may mixing holes into a fuel flow and the primary mixing zone of the combustion chamber head end. Liquid medium flow penetrates by at least 100%, but not by more than 165%, into the primary mixing zone. The liquid medium flow penetrating by more than 100% passes radially outside from the central body of the combustion chamber towards a cartridge. Multiple mixing holes are limited with a cartridge made in the combustion chamber, and interference is developed by giving specified diametre to multiple mixing holes and arrangement of many mixing holes along the cartridge in at least one of specified positions and in the specified quantity.

EFFECT: improved homogeneity of fuel and air mixture in a combustion chamber.

11 cl, 18 dwg

FIELD: power engineering.

SUBSTANCE: tubular combustion chamber comprises a mostly cylindrical jacket comprising an inner cavity, an axis and a closed end of the axis. The closed end of the axis comprises a facility to inject fuel into the inner cavity of the jacket and an impact cooling sleeve. A mostly cylindrical insert of the combustion chamber is arranged coaxially inside the jacket and is arranged so that in combination with the jacket it makes it possible to set the borders of appropriate radially external channels for flowing air for combustion and dissolving air and appropriate radially internal cavities for the combustion area and dissolution area. The combustion area is located in direction of the axis at the side of the closed end of the jacket. The dissolution area is distanced in direction of the axis from the closed end of the jacket. The impact cooling sleeve is placed coaxially between the jacket and the combustion chamber insert and stretches in direction of the axis from the closed end of the jacket practically along the entire length of the combustion zone to the closed end of the sleeve. The sleeve is equipped with a large number of holes, which have the specified size and are distributed so that they make it possible to send air for combustion to the radially external surface of the combustion chamber insert section setting the combustion zone borders, for impact cooling. The radially external surface of the insert with impact cooling is made without holes. The flow of air for combustion and dissolving air passes in radially external channels in general in direction of the axis to the closed end of the jacket. The channel for dissolving air includes a large number of dissolution ports in the combustion chamber insert to ensure arrival of the dissolving air along the radius into the dissolution zone. The combustion chamber insert and the closed end of the axis are made so that actually the entire air for combustion before it arrives into the combustion zone flows through impact cooling holes.

EFFECT: invention provides for even distribution of flow sent to swirler blades, for operation with low emission of NOx and even pre-mixing with the help of swirler blades and more efficient ratio between fuel and air for the required NOx.

8 cl, 2 dwg

Combustion chamber // 2470227

FIELD: heating.

SUBSTANCE: combustion chamber includes internal housing with sliding surface and external housing with sliding section of the wall and at least one cooling hole in the sliding section of the wall. Sliding surface and sliding section of the wall are attached to each other with possibility of sliding. Cooling hole is at least partially located in the sliding section of the wall so that it opens due to sliding movement of sliding surface in relation to sliding section of the wall when internal housing is thermally expanded, and/or closed due to sliding movement of sliding surface relative to sliding section of the wall when internal housing is thermally converged.

EFFECT: improvement of combustion chamber cooling.

7 cl, 7 dwg

FIELD: power engineering.

SUBSTANCE: turbomachine combustion chamber comprises an axis of gases flow, inner and outer circular walls, joined to each other by the chamber bottom. The inner and outer walls are accordingly equipped with at least one circumferential row of primary holes and at least one circumferential row of dissolution holes. Primary holes and dissolution holes are evenly distributed on the circumference of the inner and outer walls. All primary holes of the inner wall are arranged at one and the same axial distance (D) relative to the chamber bottom. All primary holes of the outer wall are arranged at one and the same axial distance relative to the chamber bottom. At least on one of inner or outer walls dissolution holes are distributed in the first row and in at least one second row. All dissolution holes of the first row are arranged at one and the same distance along the axis (Y) of the chamber relative to primary holes of the inner or outer wall. Primary holes are arranged in the same angular position as at least some dissolution holes of the second row, and position of dissolution holes of the first and second row arranged at the angle between two serially arranged primary holes forms a pattern that repeats along the entire circumference of the considered inner or outer wall.

EFFECT: elimination of aerodynamic relation of air jets outgoing from holes of two different types, without increase of quantity of pollutant emissions, without development of negative effect at temperature distribution at the outlet from the combustion chamber, thus optimising possibilities of repeated ignition.

17 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine combustion chamber wall includes at least one peripheral row of primary holes, at least one peripheral row of liquefaction holes and microperforation holes. All primary holes are located in one and the same axial position. Primary holes and liquefaction holes are uniformly distributed on the wall periphery. Liquefaction holes are divided at least in two different groups depending on the value of their diameter. Some part of liquefaction holes has maximum diameter, and the other part has minimum diameter. Multiperforation holes have diameters, which are smaller than minimum diameter of liquefaction holes. Liquefaction holes having maximum diameter and liquefaction holes having minimum diameter are equipped with a rear edge in the flow direction. Multiperforation holes are equipped with a front edge in the flow direction. Liquefaction holes having minimum diameter are offset in axial direction to the side of the flow movement in relation to liquefaction holes having maximum diameter. Rear edge of liquefaction holes of small diameter in the flow direction is located in one line in a circumferential direction with a rear edge of liquefaction holes in the flow direction, which have maximum diameter.

EFFECT: optimisation of arrangement of liquefaction holes; excluding the possibility of occurrence of random hot points, without increasing the quantity of polluting emissions.

5 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: annular combustion chamber (10) of turbomachine, such as aircraft turbo-jet or turboprop engine, contains coaxial walls (14, 16) in the form of rotation bodies located one inside the other with holes (66) for primary air inlet and holes (66) for mixing air inlet into the chamber. Holes for primary air inlet and holes for mixing air inlet of each wall are actually aligned with each other along the chamber longitudinal axis (34) and form a single annular set of holes (66). The chamber contains the chamber bottom (18) wall joining inlet edges of its walls (14, 16) in the form of rotation bodies and containing holes (30), in which fuel injection systems (36) and deflectors (70) are installed. The distance (L) between annular set of holes (66) and the deflector measured along the hole axis (38) is in essence equal to half of height (H) of combustion primary zone in the chamber.

EFFECT: reducing release of nitrogen oxides from turbomachine combustion chamber using simple, effective and economic method.

12 cl, 7 dwg

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