Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
  • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
  • F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/002—Wall structures
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/04—Air inlet arrangements
  • F23R3/06—Arrangement of apertures along the flame tube
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
  • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
  • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

• the invention relates to a combustion chamber housing according to the preamble of claim 1 and a gas turbine equipped with such a combustion chamber housing.
• a combustion chamber housing and a gas turbine of the type mentioned above are e.g. from DE 10 2006 042 124 A1. The one described there
• Combustor housing is part of a combustion chamber of the gas turbine and has a flame tube and a cladding tube or impact grid, which surrounds the flame tube and which in its wall a plurality of
• inflowing compressed air can penetrate radially into a gap formed between the sheath tube and the flame tube.
• Combustion chambers are designed as individual modules or as annularly arranged individual burners or as annular combustion chambers. Except for the
• Ring combustion chambers these types always have an internal, cylindrical flame tube.
• the combustion air is first sucked in atmospherically and then compressed in a compressor of a gas generator.
• the compressor may be radial or axial.
• the combustion air is then greatly deflected in order to achieve an inflow into the combustion zone. In other words, the combustion air is first the
• Combustion chamber radially in between the casing tube and flame tube supplied space formed and then deflected so that an axial inflow of the burner takes place.
• the invention is based on the object, a combustion chamber housing according to the preamble of claim 1 and a gas turbine equipped therewith
• a combustion chamber housing in particular for a gas turbine, is provided, which is a preferably circular-cylindrical flame tube and a preferably circular-cylindrical one
• Has jacket tube or impact grid which receives the flame tube and surrounds and which in its wall a plurality of
• the invention Combustor housing is characterized by a plurality of in the
• Casing tube extending longitudinal channels with preferably each
• the transverse to the flow direction of the air flowing in the operation case guide ribs cause the flow around the flame tube is interrupted or prevented.
• the air flow can distribute more evenly and the cooling of the flame tube is less disturbed.
• the cooling and combustion air is channel-shaped after the deflection from radial to axial flow, so that the inflow to a subsequent combustion zone can be made homogeneous.
• combustion chamber of a gas turbine according to the invention formed a particularly homogeneous fuel-air mixture, whereby the flame during the combustion process stable in the center of
• Combustion chamber remains A fluctuation or fluctuation of the flame would cause a local temperature increase of the surrounding components and thus a possible overuse, which is prevented by the Leitrippen.
• each guide rib is attached to the sheath tube.
• each guide rib preferably extends radially in such a way that a gap is formed between the guide rib and the flame tube
• the Letrippen are each strip-shaped, with their respective width extending radially and their respective length axially or in the longitudinal direction of the sheath tube and flame tube.
• the thickness dimension of the respective guide ribs is preferably about 3 mm.
• the guide ribs and the passage openings formed in the wall of the sheathing tube are arranged so that the guide ribs do not close any of the passage openings. This is advantageous an optimal or unobstructed radial inflow of air in the
• the guide ribs are arranged at different circumferential angular distances from one another in the intermediate space.
• the Angular spacing preferably varies in a range of about 28 degrees to about 126 degrees.
• the guide ribs comprise a first group of guide ribs and a second group of guide ribs, wherein the first group of guide ribs are arranged in a predetermined first arrangement pattern with respect to their mutual circumferential angular spacing, and wherein the second group of guide ribs are mutually circumferential
• Angular spacing are arranged in a second arrangement pattern, which is a reflection of the first arrangement pattern on an axis of symmetry of the fire tube.
• the symmetry axis preferably extends in cross section through the center of the flame tube.
• a gas turbine having a combustion chamber housing according to one, several or all of the previously described preferred embodiments of the invention is provided in any conceivable combination.
• FIG. 1 shows a perspective partially broken view of a
• FIG. 2 shows an end view of the combustion chamber housing of FIG. 1, but without a flame tube
• FIG. 3 shows a sectional view of the combustion-chamber housing of FIG. 1, seen along a line A-A in FIG.
• FIG. 4 shows in two cross-sectional views a comparison of the air flow and pressure distributions in the combustion chamber housing of FIG. 1 with and without guide ribs.
• FIGS. 1 to 4 a gas turbine 1 (not shown in full) with a combustion chamber housing 10 is shown in FIGS. 1 to 4,
• the combustion chamber housing 10 of the gas turbine 1 has a circular cylindrical flame tube 20 and a circular cylindrical sheath or baffle 30 which receives and surrounds the flame tube 20 and which has in its wall a plurality of uniformly distributed around the circumference through openings 31, on the outer circumference the
• Jacket tube 30 flowing up through a compressor (not shown) of the gas turbine 1 compressed air (cooling and combustion air) can penetrate radially into a formed between the sheath tube 30 and the flame tube 20 circular cylindrical space 40.
• a plurality in this case exactly eight) distributed circumferentially of the two tubes (flame tube 20 and sheath tube 30) arranged identical guide ribs 50 are provided, each radially between
• Sheath tube 30 and flame tube 20 and parallel to and extend along a longitudinal direction LR of sheath tube 30 and flame tube 20 so that the gap 40 through the guide ribs 50 in a plurality of
• the guide ribs 50 reliably prevent that in the operating case on the
• the guide ribs 50 are attached (e.g., welded) to the inner circumference of the jacket tube 30, with each guide rib 50 extending radially such that a gap S is formed between the guide rib 50 and the flame tube 20.
• the gap S has just such a radial width that during operation of the gas turbine. 1
• Guide ribs 50 can be compensated for on the flame tube 20.
• the guide ribs 50 are each in the form of a sheet metal strip, with their respective width extending radially and their respective length axially or in the longitudinal direction LR of the casing tube 30 and the flame tube 20.
• Thickness of the respective guide ribs 50 is about 3 mm.
• the guide ribs 50 and those formed in the wall of the jacket tube 30 are
• Interspace 40 is arranged.
• the guide ribs 50 in this case have a first group of guide ribs 50 (which are arranged in FIG. 2 to the left of an axis of symmetry Y of the flame tube 20) and a second group of guide ribs 50 (which are arranged to the right of the symmetry axis Y in FIG.
• the first group of guide ribs 50 are arranged in a predetermined first arrangement pattern with respect to their mutual circumferential angular distance
• the second group of guide ribs 50 being arranged in a second arrangement pattern with respect to their mutual circumferential angular distance, which is a reflection of the first arrangement pattern at the
• Symmetry axis Y represents
• the first and second arrangement patterns could also be completely different his.
• the specific realization of the first and second arrangement pattern or of the respective angular spacing of the guide ribs 50 can be different from the respective example B.
• Combustion chamber housing according to the upper view in Figure 4 without guide fins 50 and the combustion chamber housing according to the bottom in Figure 4 representation according to the invention with guide ribs 50 is executed.
• the guide ribs 50 which are transverse to the direction of flow of the incoming air during operation of the gas turbine 1 produce substantially homogeneous airflow and flow conditions in the intermediate space 40 due to the resulting obstruction of the circumferential flow around the flame tube 20 Pressure conditions, whereby a uniform distribution of the incoming air reaches around the flame tube 20 and the cooling of the flame tube 20 is improved.
• the air is channel-shaped after the deflection from radial to axial flow, so that the inflow to the subsequent combustion zone is homogeneous LIST OF REFERENCE NUMBERS

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Priority Applications (5)

Applications Claiming Priority (2)

Publications (1)

Family

ID=46017823

Family Applications (1)

Country Status (7)

Citations (3)

Family Cites Families (18)

• 2011
  • 2011-04-18 DE DE102011007562A patent/DE102011007562A1/de not_active Withdrawn
• 2012
  • 2012-04-16 US US14/112,464 patent/US20140144138A1/en not_active Abandoned
  • 2012-04-16 WO PCT/EP2012/056878 patent/WO2012143318A1/de not_active Ceased
  • 2012-04-16 EP EP12717246.8A patent/EP2699848B1/de not_active Not-in-force
  • 2012-04-16 CA CA2833464A patent/CA2833464A1/en not_active Abandoned
  • 2012-04-16 RU RU2013151088/06A patent/RU2544400C1/ru not_active IP Right Cessation
  • 2012-04-16 JP JP2014505582A patent/JP5678232B2/ja active Active

Patent Citations (3)

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