EP1178183A2 - Turbine à vapeur à basse pression avec un diffuseur à canaux multiples - Google Patents

Turbine à vapeur à basse pression avec un diffuseur à canaux multiples Download PDF

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Publication number
EP1178183A2
EP1178183A2 EP01117519A EP01117519A EP1178183A2 EP 1178183 A2 EP1178183 A2 EP 1178183A2 EP 01117519 A EP01117519 A EP 01117519A EP 01117519 A EP01117519 A EP 01117519A EP 1178183 A2 EP1178183 A2 EP 1178183A2
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EP
European Patent Office
Prior art keywords
diffuser
partial
channel
radial
axial
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP01117519A
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German (de)
English (en)
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EP1178183B1 (fr
EP1178183A3 (fr
Inventor
Franz Kreitmeier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Alstom Schweiz AG
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Publication date
Application filed by Alstom Technology AG, Alstom Schweiz AG filed Critical Alstom Technology AG
Publication of EP1178183A2 publication Critical patent/EP1178183A2/fr
Publication of EP1178183A3 publication Critical patent/EP1178183A3/fr
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Publication of EP1178183B1 publication Critical patent/EP1178183B1/fr
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    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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

Definitions

  • the invention relates to a low-pressure steam turbine with an axial flow axial / radial multi-channel diffuser and exhaust steam housing for low-loss guidance of the blading evaporation.
  • a diffuser of this type is described in DE 44 22 700.
  • the one revealed there The diffuser has one following the last row of blades
  • Low pressure steam turbine has an axial flow inlet and a radial one Flow outlet on.
  • the diffuser is designed to optimize the Turbine output designed by the greatest possible pressure recovery.
  • the first sections of the inner and outer diffuser ring with respect to the hub or the blade carrier at an articulation angle aligned This measure serves to make the Total pressure profile over the channel height of the diffuser in the area of the last one Blade row.
  • the diffuser has a radially outward curve Baffle that divides it into an inner and an outer channel. in the outer and inner channels are arranged flow ribs that are radial or flow diagonally.
  • the baffle serves the Redirection and also the management of the outflow.
  • the flow ribs are intended to support the guide plate and in particular to reduce it of the twist in the delay zone, which also optimizes the Contribute to pressure recovery.
  • realized flow ribs can only be used for bring about an optimal swirl reduction for a certain operating load. at a different operating load does not necessarily reduce the swirl optimal. A diffuser with this measure therefore only achieves one certain operating load an optimal pressure recovery.
  • the Flow ribs and their attachment to the baffles with a relative great design effort.
  • the supersonic interferes Crevice flow with the remaining subsonic flow.
  • EP 581 978 in particular in FIG. 4 of that document, contains a multi-channel exhaust gas diffuser for an axially flow-through gas turbine with an axial flow inlet and radial flow exit disclosed.
  • This multi-channel diffuser points along three zones in length.
  • the first zone is like a bell diffuser trained and extends single-channel from the last row of blades to Exit plane of several flow fins.
  • the diffuser rings also point here Buckling angles, which are set so that a homogenization of the Total pressure profile is reached.
  • the second zone faces downstream from the Flow ribs on flow-conducting guide rings, which have several channels form.
  • the third zone is used to strongly divert the exhaust gas flow into radial Direction and then flows into the chimney of the gas turbine. To this The purpose is the guide rings of the second zone over the length of the third zone continued, where they are curved there.
  • the second zone shows slight Redirection, but high diffuser effect on, the third zone large redirection, however only very modest diffuser effect.
  • the multi-channel diffuser should be optimized for as many operating conditions of the steam turbine as possible and be connected with a reduced design effort.
  • the exhaust steam housing should be matched to the diffuser in terms of turbine performance. This object is achieved by an axial / radial three-channel diffuser with an evaporator housing according to claim 1.
  • the three-channel diffuser has three partial diffusers, an inner, middle and outer partial diffuser, which are formed by an inner diffuser ring, an outer diffuser ring and two guide plates arranged between the diffuser rings.
  • a first section of the inner diffuser ring is arranged with respect to the hub at an inward angle towards the rotor axis and a first section of the outer diffuser ring is arranged at an angle with respect to the blade channel at the level of the last row of blades, facing away from the rotor axis ,
  • the two baffles along the entire length of the diffuser are between the inner and outer diffuser ring unevenly distributed, so that the area distribution on the three partial diffusers in the inlet surface of the diffuser is uneven.
  • the initial tangents continue to educate of the two guide plates together with the rectilinearly approximated hub-side and housing-side limits of the blading duct above the final stage of the Low-pressure steam turbine at least approximately a common one Intersection in the meridian plane.
  • the baffles are as possible located near the last row of blades, the distance between the last row of blades and the leading edges of the baffles through for everyone Operating conditions allowable minimum distance is determined.
  • the diffusion zone of the diffuser is characterized by the following features.
  • the ratio of the exit area to the entry area of the individual partial diffusers is greater than two for the middle partial diffuser and greater than three for the outer Part diffuser.
  • the corresponding is geometric Area ratio in a range from 1.5 to 1.8.
  • the ratio of its length to its length is further for the middle partial diffuser Channel height in the entrance area at least four.
  • the ratio of length to channel height in the entry area is at least equal to 10 and for the inner partial diffuser is the corresponding one Ratio at least 2.5. Because of these relatively large length-to-channel height ratios the deflections of the partial diffusers are corresponding relatively gentle.
  • the ratio of the exit area to the entry area of the entire diffuser is about two.
  • the evaporator housing of the diffuser is designed so that the size the area of the parting plane between the upper and lower half of the Evaporator housing to the size of the outlet surfaces of the partial diffusers is coordinated.
  • the two baffles are used to separate the diffuser channel into three partial diffusers, in which the blading outflow is guided. That caused Flow control is the better, the more partial diffusers for the same Total diffuser are available. On the other hand, there are more friction losses and higher blockages the more baffles are arranged.
  • the one chosen here Number, three partial diffusers and two baffles has the advantage that one optimized flow control with reasonable friction losses on the Surfaces of the baffles and blockages is effected.
  • the baffles and partial diffusers guide and stabilize the blading outflow and deflect it in a radial direction. Since the baffles extend over the entire length of the diffuser, this guidance is further supported. The radial extension of the partial diffusers also serves to naturally reduce the tangential speed. The partial diffusers are therefore optimal for all operating conditions with regard to the reduction of the tangential speed. Furthermore, the design effort for the guide plates is relatively small and no further design measures such as deflection and flow ribs are necessary to reduce the tangential speed.
  • the flow guidance and stabilization is further brought about, in particular, by the distribution of the diffuser inlet area over the three partial diffusers.
  • a large part of the inlet area is accounted for by the inner and middle channel, whereby the major part of the flow is led from the blading to the exhaust steam housing.
  • the small part of the inlet area is accounted for by the outer channel, through which the supersonic gap flow as well as the flow influenced by the gap flow is taken up from the turbine and deflected meridionally and is shielded from the majority of the flow to the evaporation housing. This shielding avoids flow interference between the majority of the flow and the high-energy gap flow, which would impair the diffuser effect.
  • the minimum distance between the last row of blades and the leading edges of the baffles further helps to optimally shield the gap flow and to avoid flow interference and streamline convergences.
  • the ratio of length to channel height of each partial diffuser of 2.5 and more enables a gentle deflection from the axial, or diagonal, to the radial flow direction, which prevents the delayed flow from separating, even with a ratio of the outlet area to the inlet area of 1.6.
  • the design of the diffuser according to the invention is based on an inverse Design process in which the predominant flow fields be determined. Then the ideal ones are created Flow fields are calculated and the geometry of the diffuser based on this ideal flow fields is determined.
  • this three-channel diffuser designed for limit load conditions. At limit load was a Flow field determined for which a three-channel diffuser with an orientation of Initial tangent of his guide plates according to the invention the highest Pressure recovery achieved. Through experimental evidence, this is from this Design resulting geometry in the entire operating range of the turbine Superior diffusers of the prior art. This interpretation also provides the advantage that a higher turbine output with the same Capacitor pressure is achieved or that the same turbine output at higher Condenser pressure is achieved and thus a smaller, cheaper Cooling system for the steam turbine is required.
  • the initial tangents of the guide plates lie in an angular range around the first kink points of the guide plates and around a reference initial tangent, which at least approximately lead through the first kink point of the guide plate and through the intersection of the rectilinearly approximated boundaries of the blade channel.
  • the outer one is used Partial diffuser a share of the total flow inlet area of the diffuser in the Range of 10-12%. The remaining entry area is 55-60% on the inside Partial diffuser and 30-35% distributed in the middle part diffuser.
  • the distance between the leading edges of the guide plates and the trailing edge of the last moving blade is 4% of the total height of the running row.
  • the front edges of the guide plates are profiled at the flow inlet of the diffuser, which causes a gentle acceleration when entering the partial diffusers.
  • the diffusion zone of the diffuser is characterized as follows.
  • the baffles are each supported by struts or supports that extend from the inner and outer diffuser ring to the two baffles.
  • the middle partial diffuser remains free of supports and therefore has minimal flow disturbances and losses.
  • evaporation zone of the diffuser is on End baffle between the inner and middle partial diffuser in a radial Extending an evaporation baffle.
  • This exhaust steam baffle causes a better flow distribution in the evaporation housing, whereby the Flow losses are minimized and the condenser is charged more evenly becomes.
  • Figure 1 shows a three-channel diffuser as part of a low-pressure steam turbine. It leads the blading outflow into an exhaust steam housing 20.
  • the low pressure steam turbine shows the rotor 1 with the rotor axis 2 and a rotor blade 3 of the last row of rotor blades.
  • the three-channel diffuser is delimited by an inner diffuser ring 4 and an outer diffuser ring 5.
  • the outer diffuser ring 4 is connected to the blade carrier 7.
  • the inner and outer diffuser rings 4 and 5 have kink angles ⁇ N and ⁇ Z in the region of the rear edge of the rotor blade, wherein, as shown in FIGS.
  • the angle ⁇ N through the first section 4 'of the inner diffuser ring 4 and an extension of the hub 6 and the angle ⁇ Z are formed by the extension of the last section 7 'of the blade carrier 7 and the first section 5' of the outer diffuser ring 5.
  • These kink angles are, for example, 10-20 ° and help to ensure that a total pressure profile that is as homogeneous as possible is achieved at the outlet of the last row of blades.
  • the inside of the diffuser has two guide plates 8 and 9, which divide the diffuser into three subchannels, an inner partial diffuser 10, a central partial diffuser 11 and an outer partial diffuser 12.
  • the baffles are supported by supports 13 which extend from the inner and outer diffuser rings 4 and 5 to the baffles.
  • the first supports 13 in the direction of flow are thicker than the second supports and each have a round cross section.
  • the middle partial diffuser 10 is in particular free of supports.
  • the baffles are distributed over the channel height of the diffuser in consideration of the total pressure profile in such a way that an aerodynamically optimal surface distribution over the three subchannels is achieved.
  • the first guide plate 8 is arranged in such a way that the inner partial diffuser 10 has a flow entry area which is, for example, approximately 60% of the flow entry area of the entire diffuser.
  • the second guide plate 9 is further arranged such that the central partial diffuser 11 has, for example, a flow entry area of approximately 30% of the total flow entry area.
  • the outer partial diffuser 12 has a flow inlet area of, for example, approximately 10% of the total flow inlet area.
  • the diffuser exit area is designed such that the ratio of the exit area to the entry area of the entire diffuser, that is to say its upper and lower half, is approximately 2.
  • the geometric relationships from the outlet to the inlet surface are as follows.
  • the ratio of the exit area S12 in the upper half of the diffuser to the entry area S11 is approximately 1.3.
  • the ratio of exit area S13 in the lower half of the diffuser to entrance area S11 is larger and is approximately 1.6.
  • the exit surface S13 of the inner partial diffuser 10 is therefore further out in the lower half of the diffuser than in the upper half. (Although it is actually in the lower half of the diffuser, it is also shown in this figure and in FIG. 4 with S13.)
  • the ratio of the exit area S22 to the entry area S21 is approximately 2.1.
  • the ratio of outlet area S32 to inlet area S31 is approximately 3.3. Such area ratios are the prerequisite for significantly increasing the efficiency of the turbine.
  • the diffuser is designed with a view to smoothly guiding the flow low curvature in relation to the channel height.
  • the three Partial diffusers have a large length-to-channel height ratio. This is for the inner partial diffuser 10, for example, greater 2.7 in the lower half of the diffuser.
  • For the middle and outer partial diffuser 11 and 12 are the Ratios greater than 4.4 or greater than twelve in the example shown.
  • the inner and outer diffuser ring as well as the two baffles point in their Cross section for manufacturing reasons several straight sections, due to the large length-to-channel height ratios in gentle Angles of inclination to each other. Allow this gentle angle of inclination improved guidance of the blading outflow. It will Avoided flow interference and flow separation in particular. Due to the relatively large radial extension of the diffuser and the Partial diffusers also become a natural breakdown of tangential speeds without the help of additional flow ribs or other measures Reductions in tangential speeds achieved.
  • the three partial diffusers have a gentle deflection due to their radial extension.
  • the total deflection of each partial diffuser is indicated by the angles ⁇ 1 , ⁇ 2 and ⁇ 3 in the center line 15 of the individual partial diffusers 10, 11 and 12, respectively. These angles are, for example, approximately 70 °, 36 ° or 47 °.
  • the guide plates 8 and 9 are approximately designed so that the extension of their initial tangents form the intersection A.
  • the rectilinearly approximated hub-side and housing-side boundary of the blade channel also runs through this intersection point A.
  • the starting tangents of the guide plates 8 and 9 are oriented at angles ⁇ 1 and ⁇ 2 with respect to the rotor axis 2.
  • the intersection A between the linearly approximated hub-side and housing-side limits of the blading duct via the final stage of the turbine and the initial tangents of the guide plates 8 and 9 form an at least approximately common intersection.
  • the initial tangent of the guide plate 8 forms an angle in the range of ⁇ 1 + 8 ° with the straight-line approximated hub-side limit.
  • the initial tangent of the guide plate 9 accordingly forms an angle in the range of ⁇ 2 ⁇ 4 °.
  • This geometrical design of the guide plates with regard to the limits of the blading duct also applies to other housing contours and blade types, such as for example for completely conical rectilinear housing contours, for housing contours in which the section runs cylindrical or almost cylindrical over the last row of blades.
  • This geometry can also be used not only for blades with a tip seal, but also for blades with shrouds. In this case, the housing-side boundary of the blade channel runs through the intersection of the rear edge of the last blade and the shroud.
  • the diffuser rings 4 and 5 and baffles 8 and 9 exist in the example shown from several straight sections that are at small angles to each other are standing together. Instead of sections are also continuous curved baffles and diffuser rings can be realized.
  • the partial diffusers 10 and 11 are arranged in such a way that a major part of the flow flows from the blading through these two partial diffusers into the exhaust steam housing 20.
  • a stable guidance of the main part of the flow in the area of the middle partial diffuser is most sensitive to obstructions due to the Mach numbers prevailing there.
  • the high-energy, supersonic gap flow from the last rotor blade row reaches the outer partial diffuser 12, the channel height of which is determined in relation to the prevailing gap flow.
  • the gap flow is conducted through the outer partial diffuser 12 separately from the main part of the flow into the exhaust steam housing 20.
  • the large length-to-channel height ratio stabilize the Diffuser flow and homogenization and lowering of the Total pressure profile at the level of the last row of blades. This will make the Pressure recovery of the diffuser increases and an increase in efficiency whole low pressure steam turbine reached.
  • the baffles 8 and 9 extend at the entrance to the diffuser up to close to the row of blades. They are preferably arranged as close as the axial, thermal movements of the rotor blade row and a safety distance required for the various operating conditions allow, without causing rubbing.
  • the distance a between the front edges of the guide plates 8 and 9 and the rear edge of the last rotor blades is 3 4% of the total height h w of the last rotor blade row.
  • the front edges of the baffles 8 and 9 are profiled in order to enable a smooth flow entry into the partial diffusers with the lowest possible overspeeds. The front edges are, for example, as shown in FIG.
  • the guide plates are made as thin as possible so that the Mach numbers increase as little as possible.
  • their thickness is, for example, approximately 5% of the channel height of the central partial diffuser 11.
  • an exhaust steam guide plate 8 ' is arranged on the guide plate 8 between the inner and middle partial diffuser in a radial extension.
  • This exhaust steam guide plate 8 ' brings about an improvement in the flow in the exhaust steam housing 20 and a more uniform flow in the condenser.
  • the steam guide plate 8 ' has a gentle total deflection ⁇ L of approximately 50 °. In this exemplary embodiment, this deflection is realized by two sections, the total length of which is approximately 0.7 to the channel height in the exit plane.
  • FIG. 3 shows a cross section through the exhaust steam housing 20 with an upper one Half 21 and a lower half 22 separated by a parting plane 23 are separated.
  • the turbine steam passing through the exit surface of the top half of the diffuser in the upper half 21 of the evaporation housing 20 flows then down through the parting plane 23 into the lower half 22 and from there through the exit surface 24 of the evaporator housing in the connected there Capacitor.
  • the evaporation housing is designed in coordination with the diffuser so that the Exit surface 24 of the evaporation housing 20 is about 15% larger than that Total outlet area of the diffuser is. This grants an area reserve in the Separation level for any obstructions in the outflow.
  • the sum of the exit areas of the partial diffusers 11 and 12 is the upper half of the diffuser is approximately equal to the area 25 in the parting plane 23, which between the evaporation housing and the evaporation baffle 8 'of Baffle 8 is formed and hatched in the figure with solid lines is.
  • half of the exit surface S12 of the inner partial diffuser 10 over the entire Rotation of the diffuser is equal to the area 26 hatched by dashed lines.
  • the alignment of these surfaces causes the diffuser outflow of the Partial diffusers 11 and 12 as they emerge from the diffuser into the exhaust housing the flow area is as large as possible and there are no bottlenecks. This in turn has a positive effect on pressure recovery.
  • FIG. 5 shows a variant of the three-channel diffuser according to the invention with an exhaust steam housing, which is optimized in comparison to the configuration in FIG. 1.
  • the optimized diffuser with exhaust steam housing is designed, in particular with regard to the inner partial diffuser, in such a way that the outlet surface S12 'of the inner partial diffuser 10 is further defined in comparison to the configuration in FIG. If the exit surface S12 'is further out, as indicated by the dashed line, the ratio of the exit surface to the inlet surface of that partial diffuser increases and the efficiency of the turbine is increased accordingly.
  • the exit area S12 ' is defined in such a way that the ratio of its area to the entry area S11 increases to approximately 1.8, which is a significant increase compared to the ratio of approximately 1.3 in the variant of FIG.
  • the wall 21 'or hood of the upper half of the exhaust steam housing is placed radially further outwards in comparison to the wall 21 of the exhaust steam housing from FIG.
  • the baffle 27 'of the exhaust steam housing is placed axially further out. Accordingly, the deflection ⁇ 1 reduced compared to the deflection angle in Figure 1 to about 60 degrees.
  • FIG. 6 shows this variant in the parting plane 23 between the upper and lower half of the diffuser. This also shows how the dimensions of the exhaust steam housing and the sizes of the outlet surfaces of the partial diffusers are coordinated.
  • the diffuser is designed such that half of the exit surface S12 'of the inner partial diffuser 10 is approximately equal to the hatched area 28 in the parting plane 23 between the upper and lower half of the diffuser over the entire rotation of the diffuser.
  • the surface 28 is formed by the baffle wall 27 'arranged axially further outwards, the hood 21' placed radially further outwards, a wall 31 facing the turbine and the exhaust-gas baffle 8 '.
  • the surface 28 is finally closed by a fictional axially extending line 30 between the exhaust steam guide plate 8 'and the wall 31. Furthermore, the sum of the exit areas S22 and S32 of the other two partial diffusers is approximately equal to the hatched area 29 in the parting plane. This surface 29 is the evaporation baffle 8 ', formed by the line 30, the wall 31. Furthermore, the exit surface S13 'in the lower half of the diffuser in this case falls on the same location as the exit surface S12' for the upper half of the diffuser.
EP01117519A 2000-07-31 2001-07-20 Turbine à vapeur à basse pression avec un diffuseur à canaux multiples Expired - Lifetime EP1178183B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10037684 2000-07-31
DE10037684A DE10037684A1 (de) 2000-07-31 2000-07-31 Niederdruckdampfturbine mit Mehrkanal-Diffusor

Publications (3)

Publication Number Publication Date
EP1178183A2 true EP1178183A2 (fr) 2002-02-06
EP1178183A3 EP1178183A3 (fr) 2003-07-23
EP1178183B1 EP1178183B1 (fr) 2005-05-11

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EP01117519A Expired - Lifetime EP1178183B1 (fr) 2000-07-31 2001-07-20 Turbine à vapeur à basse pression avec un diffuseur à canaux multiples

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US (1) US6533546B2 (fr)
EP (1) EP1178183B1 (fr)
JP (1) JP4791658B2 (fr)
DE (2) DE10037684A1 (fr)

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EP1892384A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Diffuseur pour une turbine à vapeur
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur
WO2012089837A1 (fr) * 2010-12-30 2012-07-05 Duerr Cyplan Ltd. Turbomachine
US8506233B2 (en) 2009-09-14 2013-08-13 Alstom Technology Ltd. Axial turbine and method for discharging a flow from an axial turbine
EP2639404A1 (fr) * 2012-03-14 2013-09-18 General Electric Company Diffuseur d'échappement d'une turbine
WO2014158338A1 (fr) * 2013-03-13 2014-10-02 General Electric Company Système d'échappement d'un diffuseur radial
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US8591185B2 (en) 2010-11-16 2013-11-26 General Electric Company Low pressure exhaust gas diffuser for a steam turbine
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US20130022444A1 (en) * 2011-07-19 2013-01-24 Sudhakar Neeli Low pressure turbine exhaust diffuser with turbulators
US20140037439A1 (en) * 2012-08-02 2014-02-06 General Electric Company Turbomachine exhaust diffuser
US9388710B2 (en) 2012-10-01 2016-07-12 General Electric Company Exhaust diffuser arrangement for a turbine system and method of redirecting a flow
US9784283B2 (en) * 2014-06-06 2017-10-10 Baker Hughes Incorporated Diffuser vanes with pockets for submersible well pump
WO2016014291A1 (fr) * 2014-07-21 2016-01-28 American Recreation Products, LLC. Sac à dos ayant une expansion horizontale
EP3054086B1 (fr) * 2015-02-05 2017-09-13 General Electric Technology GmbH Configuration de diffuseur de turbine à vapeur
US10041377B2 (en) 2015-11-24 2018-08-07 General Electric Company System and method for turbine diffuser
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JP6731359B2 (ja) 2017-02-14 2020-07-29 三菱日立パワーシステムズ株式会社 排気ケーシング、及びこれを備える蒸気タービン
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CN110685756B (zh) * 2019-10-10 2022-03-15 中国船舶重工集团公司第七0五研究所 一种低流动压力损失异形渐变排气结构
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EP1892384A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Diffuseur pour une turbine à vapeur
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur
WO2008110445A1 (fr) * 2007-03-13 2008-09-18 Siemens Aktiengesellschaft Dispositif diffuseur
US8506233B2 (en) 2009-09-14 2013-08-13 Alstom Technology Ltd. Axial turbine and method for discharging a flow from an axial turbine
EP3480425A1 (fr) * 2010-12-30 2019-05-08 Duerr Cyplan Ltd. Turbomachine
WO2012089837A1 (fr) * 2010-12-30 2012-07-05 Duerr Cyplan Ltd. Turbomachine
EP2639404A1 (fr) * 2012-03-14 2013-09-18 General Electric Company Diffuseur d'échappement d'une turbine
WO2014158338A1 (fr) * 2013-03-13 2014-10-02 General Electric Company Système d'échappement d'un diffuseur radial
US9644496B2 (en) 2013-03-13 2017-05-09 General Electric Company Radial diffuser exhaust system
EP2971617A1 (fr) * 2013-03-13 2016-01-20 General Electric Company Système d'échappement d'un diffuseur radial
EP2971617B1 (fr) * 2013-03-13 2021-05-26 General Electric Company Système d'échappement d'un diffuseur radial
WO2019052874A1 (fr) * 2017-09-14 2019-03-21 Abb Turbo Systems Ag Diffuseur d'une turbine à gaz d'échappement
KR20200049843A (ko) 2017-09-14 2020-05-08 에이비비 터보 시스템즈 아게 배기 가스 터빈의 디퓨저
US11073048B2 (en) 2017-09-14 2021-07-27 Abb Schweiz Ag Diffuser of an exhaust gas turbine

Also Published As

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DE10037684A1 (de) 2002-02-14
JP4791658B2 (ja) 2011-10-12
DE50106175D1 (de) 2005-06-16
EP1178183B1 (fr) 2005-05-11
EP1178183A3 (fr) 2003-07-23
JP2002081301A (ja) 2002-03-22
US20020127100A1 (en) 2002-09-12
US6533546B2 (en) 2003-03-18

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