Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/30—Exhaust heads, chambers, or the like
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
  • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
  • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
  • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor

Definitions

• the invention relates to a gas turbine with an adjoining a turbine unit exhaust diffuser, whose diffuser channel is bounded by a wall outside and on which a number of inwardly extending hollow support ribs for mounting a radial bearing of the gas turbine are provided, wherein the exhaust gas Diffuser at least one pipeline comprehensive Abblasetechnisch for blown air outflow en ⁇ det, whose inflow-side end is connected to a compressor of the gas turbine.
• Gas turbines and their modes of operation are well known from the widely available state of the art. They always include an exhaust gas diffuser as part of an exhaust gas line, through which the exhaust gas flowing out of the gas turbine can be continued. The exhaust gas is either led to a chimney, if the gas turbine for single operation, called in English Simple Cycle, is provided. In a combined-cycle power plant - called Combined Cycle in English - leads the Abgasasstre ⁇ bridge the exhaust gas to a boiler, with the help of which the thermal energy contained in the exhaust gas is converted into steam for a steam turbine.
• the operating point of the exhaust diffuser depends primarily on its volume flow. This is known to be mainly influenced by the ambient temperature, the compressor inlet guide vane position and the firing temperature.
• the exhaust diffuser should meet several requirements: Firstly, a maximum pressure recovery is required for maximum efficiency at the design point. At the same time, the efficiency will drop only slightly when removed from the off ⁇ legungstician if possible. To the Others, he should have no unsteady operating behavior, which otherwise could affect the mechanical integrity of the power plant ⁇ by vibration excitation. In addition, it should have as uniform a velocity distribution as possible at the outlet to achieve a good boiler efficiency. Equally important is the avoidance of flip-flop effects when changing the operating point during deep part-load operation. Finally ⁇ Finally, the exhaust diffuser should also be small-sized and therefore inexpensive.
• the object of the invention is therefore to provide a gas turbine with a subsequent to a turbine unit exhaust diffuser, which can counteract the problems mentioned in the prior art.
• the downstream end of the blow-off line is fluidically connected via the hollow space of the support ribs connected to the hub for forwarding Abblaseluft to the hub and the Abblase poverty is blown on the hub side to the reverse flow behind the hub re ⁇ appear or as Coanda Beam to reduce the tendency to detach at a possibly tapered hub end.
• the outflow-side end of the blow-off line is fluidically connected to the cavity of the support ribs, wherein the support ribs have openings for blowing the blow-off air into the diffuser channel.
• the support ribs which Abblase poverty can be specifically used for reducing the detachments of the then heavily misused flocked support ribs in partial load operation. Furthermore, in this way, the bearing star formed by the support ribs and parts thereof-for example, their sheet metal clothing-can be specifically cooled. This allows an increase in the turbine outlet temperature in the part-load operation, compared to the rated load operation, whereby in part-load operation again the lowering of the flame temperature and the associated increase in the CO values of the exhaust gas can be counteracted. It should be noted that the blowing out of the blow-off air through the openings arranged in the support ribs can also be provided independently of the blowing through the hub.
• the invention will be explained in more detail with reference to a single FIGURE.
• the single embodiment shows a gas turbine in a longitudinal section.
• FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
• the gas turbine 10 has inside a rotatably mounted about a rotation axis 12 rotor 14, which is also referred to as a turbine runner.
• a rotation axis 12 rotor 14 Along the rotor 14 follow one another an intake housing 16, a Axialturbover Noticer 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetric symmetrically arranged to each other burners 22, a turbine unit 24 and a turbine outlet housing 26 to the turbine outlet housing 26 of the gas turbine 10 is followed by a not shown turbines -Abgas distributor on. Both components are part of the gas turbine exhaust diffuser 21.
• the gas turbine can also be equipped with multiple tube combustion chambers.
• the Axialturbover Noticer 18 comprises a ring-shaped channel compressor in successive cascade constricting compressor stages from Laufschaufei- and vane ⁇ wreaths.
• the rotor blades 14 arranged on the blades 27 are located with their free-ending blade tips of an outer channel wall of the compressor passage opposite.
• the compressor channel opens via a compressor outlet diffuser 36 in a ple number 38.
• the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas channel 30 of the turbine unit 24.
• Turbi ⁇ nenech 24 are four successive turbine arranged steps 32.
• a generator or a working machine (each not shown) is coupled.
• the turbine output housing 26 of the gas turbine 10 is followed by a turbine exhaust manifold. Both components are part of the gas turbine exhaust diffuser 21. Downstream of the Turbi ⁇ nen exhaust manifold, an equally not dargestell ⁇ tes exhaust gas system is provided. This and the gas turbine exhaust diffuser 21 form the exhaust gas diffuser system.
• an inflow-side annular diffuser channel 33 is provided, which is bounded radially on the outside by a conical channel wall 40.
• a conical channel wall 40 On the channel wall 40 along the periphery of the diffuser channel 33 six
• Support ribs 35 distributed, of which only one is shown in longitudinal section. There may also be a different number of support ribs.
• Each support rib 35 has in its interior a support 37, which is protected by a Blechumposed 39 from direct contact with exhaust gas.
• the Blechumposed 39 has a leading edge 41 and a Ab ⁇ strömkante 43, which is profiled aero ⁇ dynamically in cross section analogous to the profile contour of a blade of a compressor blade.
• a hub 48 is arranged, which forms a housing for an internally disposed turbine-side radial bearing 51.
• blow-off 47 a part of the compressor mass flow feed ⁇ bar.
• the blow-off line 47 comprises three pipes, of which only one pipe is shown. It can also be provided more than three or fewer pipes.
• the pipes, not shown, are distributed along the circumference of the gas turbine 10.
• a valve is also provided as an actuator 46 for closing and partially or completely opening the pipelines. All pipes connect the compressor 18 or the plenum 38 with the cavities 45 to supply this blow-off air.
• a plurality of openings 49 are provided, through which the supporting rib, a ⁇ can be brought 35 supplied Abblase Kunststoff in the diffuser channel 33rd
• openings 49 may be provided for blowing blown air in the hub. In particular, the latter embodiment is suitable for avoiding return flow zones downstream of the hub 48.
• the operation of the gas turbine 10 is designed so that in nominal load operation only such an amount of blow-off air flows out of the openings 49 as is necessary to prevent penetration of the exhaust gas into the openings 49. If the power output of the gas turbine is lowered below a predetermined value, which is arranged in the Abblaselei ⁇ tung actuators 47 are further opened 46 so that the Abblasemassenstrom significantly increases.
• the predetermined value may, for example, 80%, 70%, 50% or even a ande ⁇ ren percentage of gas turbine rated power amount.
• detachment at the support ribs 35 can be avoided by this measure. ner Benedictanströmung can occur because of a reduced exhaust gas mass flow.
• the percentage of combustion air in the fuel-air mixture is reduced, which leads to a higher combustion temperature and can keep CO emissions to a lower level.
• blowing out the blow-off air through the hub 48 can also remindströmzonen downstream of the hub 48 can be avoided.
• the invention proposes a gas turbine 10 with an exhaust gas diffuser 21 adjoining a turbine unit 24, whose diffuser channel 33 is bounded on the outside by a channel wall 40 and on which a number of inwardly extending hollow support ribs 35 for fastening a radial bearing 51 the gas turbine 10 are provided, wherein at the exhaust gas diffuser 21 at least one pipes comprehensive Abblasetechnisch 47 for blown air ends outflow, the ⁇ sen inflow end is connected to a compressor 18 of the gas turbine 10.
• the support ribs 35 have a hub 48 at their inner end, at the axial end thereof further openings 49 for blowing out the blow-off air into the diffuser duct are pre ⁇ seen.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Supercharger (AREA)

Priority Applications (6)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

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Citations (6)

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• 2012
  • 2012-02-28 EP EP12157273.9A patent/EP2634381A1/de not_active Withdrawn
• 2013
  • 2013-01-15 US US14/376,429 patent/US20140373504A1/en not_active Abandoned
  • 2013-01-15 EP EP13700689.6A patent/EP2791478A1/de not_active Withdrawn
  • 2013-01-15 KR KR1020147024186A patent/KR20140127291A/ko not_active Withdrawn
  • 2013-01-15 JP JP2014559129A patent/JP2015508860A/ja not_active Ceased
  • 2013-01-15 WO PCT/EP2013/050610 patent/WO2013127553A1/de not_active Ceased
  • 2013-01-15 IN IN6201DEN2014 patent/IN2014DN06201A/en unknown
  • 2013-01-15 CN CN201380011492.8A patent/CN104145089B/zh not_active Expired - Fee Related

Patent Citations (6)

Non-Patent Citations (1)

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