EP0581978A1 - Diffuseur à zones multiples pour turbomachine - Google Patents

Diffuseur à zones multiples pour turbomachine Download PDF

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Publication number
EP0581978A1
EP0581978A1 EP92113180A EP92113180A EP0581978A1 EP 0581978 A1 EP0581978 A1 EP 0581978A1 EP 92113180 A EP92113180 A EP 92113180A EP 92113180 A EP92113180 A EP 92113180A EP 0581978 A1 EP0581978 A1 EP 0581978A1
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EP
European Patent Office
Prior art keywords
diffuser
zone
flow
ribs
diffusion zone
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
EP92113180A
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German (de)
English (en)
Other versions
EP0581978B1 (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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to DE59204947T priority Critical patent/DE59204947D1/de
Priority to EP92113180A priority patent/EP0581978B1/fr
Priority to US08/098,814 priority patent/US5338155A/en
Priority to JP19225493A priority patent/JP3416210B2/ja
Publication of EP0581978A1 publication Critical patent/EP0581978A1/fr
Application granted granted Critical
Publication of EP0581978B1 publication Critical patent/EP0581978B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • Such multi-zone diffusers for turbomachinery are known from EP-A 265 633.
  • a rectifying grating is provided within the diffuser, which extends over the entire height of the channel through which flow passes .
  • These means for swirl removal are cylindrical flow ribs arranged uniformly over the circumference with thick straight profiles, which are designed according to the knowledge of turbomachine construction and which should be as insensitive as possible to oblique flow. The leading edge of these ribs is located relatively far behind the trailing edge of the last blades in order to avoid excitation of the last row of blades caused by the pressure field of the ribs.
  • This distance is dimensioned such that the front edge of the ribs is in a plane in which a diffuser area ratio of preferably three predominates.
  • This first diffusion zone between the blading and the flow ribs should thus remain undisturbed due to total rotational symmetry.
  • the fact that no interference effects between the ribs and the blades are to be expected is due to the fact that the ribs only become effective in a plane in which a relatively low speed level already prevails.
  • the known diffuser for supporting the flow in the radial direction is divided into several partial diffusers by means of flow-guiding rings.
  • These guide rings extend from a level directly at the exit of the blading to a level at which a diffusion ratio of three has been reached, i.e. over the entire first diffusion zone.
  • these guide rings should preferably be formed in one piece. This leads to a solution which is disadvantageous for assembly reasons, without a parting plane.
  • the guide rings lead to large diameters, so that transport problems can arise.
  • a second diffusion zone extends from the front edge of the thick flow ribs to the greatest profile thickness of the ribs. In this second zone, the swirling of the flow is to be carried out for the most part, largely without delay. In a third subsequent diffusion zone in the form of a straight diffuser there is a further delay in the flow, which at the time was almost swirl-free.
  • the diffuser is flowed at at idle under a speed ratio c t / c n of approximately 1.2, where c t means the tangential speed and c n the axial speed of the medium. This oblique flow leads to a drop in the pressure recovery C p .
  • the large drop in pressure recovery can be attributed to the fact that, under the extreme conditions mentioned, a strong vortex is formed between the outlet blades and flow ribs.
  • the vortex is limited by the flow ribs on which the tangential component of the velocity is dissipated. If solid particles, for example in gas turbines or water droplets, for example in steam turbines, are carried along with the return flow, an acute risk of foot erosion can arise on the blades of the last run row.
  • the object of the invention is for a multi-zone diffuser of the type mentioned at the given diffuser area ratio, which is understood to mean the ratio of the flow cross sections at the outlet to the inlet of the diffuser, and with the smallest possible diameter in the first diffusion zone as well as with the physically greatest possible pressure recovery and swirl-free flow, to keep the total length of the diffuser to a minimum.
  • the advantage of the invention is to be seen, inter alia, in the fact that the bend angle idea can be carried out for the first time by means of a single-channel diffuser in the case of a strongly divergent flow.
  • the ratio of the rib spacing a from the exit of the blades to the rib pitch t is at least 0.5. This measure also results in a full utilization of the working ability of the fluid.
  • the ratio of rib chord s to rib pitch t is at least 1, it is ensured that the sensitive diffuser flow is free of detachment in the axial outflow direction is redirected and that a contribution to the desired delay is made.
  • the ratio of the greatest profile thickness d max of the flow ribs to the rib chord s is at most 0.15 and is largely constant over the rib height, overspeeds, local Mach number problems and different displacement effects are minimized.
  • the curvature of the Velcro line of the ribs is advantageously chosen with regard to a smooth entry and an axial outflow. This guarantees the desired high pressure recovery as well as a certain insensitivity to partial load.
  • the meridian contour of the diffuser in the region of the ribs is additionally expanded in order to avoid overspeeds on the ribs.
  • the displacement effect caused by the ribs is compensated for at least in the peripheral zones.
  • the diffuser is provided with a horizontal parting plane in the first diffusion zone. Due to the fact that, in contrast to the solution mentioned at the beginning, the first diffusion zone is not equipped with guide rings, which are usually made in one piece for reasons of vibration, thanks to the parting plane it is possible to cover the first zone and thus easy assembly and disassembly, for example, of the blading guaranteed without auxiliary devices and without axial displacement.
  • ribs In the case of a parting plane in the first diffusion zone, an even number of ribs is provided, ribs being arranged in the vertical plane, but not in the horizontal plane.
  • the lower vertical rib can thus be used to support the diffuser and there is no need for split ribs.
  • the same elements are each designated with the same reference symbols, but with different indices.
  • the embodiment shown in FIGS. 1, 2 and 3 has no indices.
  • the articulation angles are designated as such only in FIG. 2.
  • the direction of flow of the working fluid is indicated by arrows.
  • the gas turbine of which only the last three axially flowed stages are shown in FIG. 1, essentially consists of the bladed rotor 1 and the vane carrier 2 equipped with guide blades.
  • the vane carrier is suspended in the turbine housing 3.
  • the rotor lies in a support bearing 4, which in turn is supported in an exhaust housing.
  • this exhaust housing essentially consists of a hub-side inner part 6 and an outer part 7, which limit the diffuser 13.
  • Both elements 6 and 7 are pot housings with a horizontal parting plane at shaft height. They are connected to one another by a plurality of welded supporting flow ribs 8, which are evenly distributed over the circumference and whose profile is indicated by 9.
  • the exhaust housing is designed so that it is not in contact with the exhaust gas flow.
  • the actual flow control is taken over by the diffuser, which is designed in its first zone as an insert for the exhaust housing.
  • the outer boundary wall 14 and the inner boundary wall 15 of the diffuser are held over the flow ribs 8.
  • the walls are penetrated by actual support bodies 10 which extend within the flow ribs and hold the exhaust gas housing 6, 7.
  • the decisive factor for the desired functioning of the diffuser is now the kink angle of its two boundary walls 14 and 15 directly at the exit of the blading.
  • This is a highly loaded reaction blading with a large opening angle.
  • a high Mach number flows through the last row of blades.
  • the channel contour on the blade root is cylindrical, that on the blade tip runs obliquely at an angle of approx. 30 °. If this conicity were to be continued in the diffuser, the angle of 30 ° mentioned would be completely unsuitable in order to delay the flow and to achieve the desired pressure increase.
  • the current would detach from the walls. Purely constructive considerations would normally lead to a reduction of the diffuser angle from 30 ° to 7 °.
  • the diffuser is therefore designed solely on the basis of fluid dynamics. The considerations must lead to achieving the most homogeneous possible total pressure profile over the entire channel height, i.e. also on the hub and on the cylinder. The two bending angles are therefore determined on the basis of the entire flow in the blading and in the diffuser.
  • the total opening angle of the diffuser is in the range of the opening angle of the blading, and may even be greater than this. Under no circumstances does it assume a value that would correspond to purely constructive considerations.
  • the channel is therefore divided in the radial direction by means of flow-guiding rings into a plurality of partial diffusers which are dimensioned according to the known rules.
  • the first diffusion zone 50 extends from the exit plane of the last row of blades to a plane at the outlet of the flow ribs 8.
  • the latter are therefore included and their type, their design, their arrangement and their number based on the following considerations.
  • the distance a from the leading edge 24 of the flow ribs 8 to the exit of the blading is set in relation to the rib pitch t - which is the measure for the number of ribs. If this ratio is at least 0.5, interference with the last row 12 of the blading can be largely avoided.
  • the minimum cross-section should not be undercut. Sufficient space must be created in the interior of the ribs for the arrangement of the supporting bodies 10.
  • a minimum chord length should also not be undercut. Now the ratio of rib chord s to Rib division t at least 1, so both tasks can be performed.
  • the first diffusion zone 50 is provided with a horizontal parting plane, i.e. the outer boundary wall 14 and the inner boundary wall 15 of the diffuser are designed to be divided. No flow ribs are preferably installed in this horizontal parting plane in order to avoid a division of the ribs. On the other hand, it is advisable to arrange flow ribs in the vertical plane.
  • the vertically oriented flow rib of the lower half can thus be used for support functions.
  • the ratio of the greatest profile thickness d max of the flow ribs to the rib chord s should not exceed 0.15 and is kept largely constant over the rib height.
  • the flow ribs are curved.
  • the curvature of the Velcro line of the ribs is with regard to a shock-free entry and an axial one Outflow selected, which leads to a variable curvature above the rib height.
  • the front edges 24 of the ribs are oriented above the rib height so that they are cut perpendicularly by the streamlines. This leads to leading edges, which in no way have to be aligned radially, as illustrated in FIG. 3.
  • the meridian contour of the diffuser in the area of the ribs 8 is additionally expanded. At least this measure is taken in the area 25 from the front rib edge 24 to the greatest profile thickness. In this way, overspeeds on the ribs can be largely avoided.
  • This first diffusion zone 50 which ends at the outlet of the flow ribs, is designed with an area ratio of 1.8.
  • a second diffusion zone 51 in the form of a multi-channel diffuser part adjoins the first diffusion zone. It is designed with an area ratio of 2.5.
  • two flow-guiding rings 16 are arranged downstream of the ribs 8, which divide the channel into three partial diffusers 17.
  • L is the axial extent of the second diffusion zone
  • L 1K is the axial extent of one single-channel diffuser with the same area ratio
  • n the number of partial diffusers.
  • this second diffusion zone 51 there are three profiled hollow ribs 18 distributed uniformly over the circumference, one of these hollow ribs standing vertically in the upper half. Electrical, air and oil lines can be passed through these hollow ribs.
  • the blunt trailing edges of these hollow ribs are provided with defined tear-off edges 19.
  • the annular inner boundary wall 15 of the diffuser which ends at the outlet of the second diffusion zone 51 with a blunt section 20, is also provided with such a defined tear-off edge 21.
  • this second diffusion zone 51 has a considerably larger diameter than the first diffusion zone 50.
  • the second zone is merely a sheet metal construction which can be assembled from disassembled parts at the installation site of the system, this fact offers in particular no difficulties with the rail transport.
  • a third diffusion zone 52 in the form of an impact diffuser is provided downstream of the second diffusion zone 51, this being a sudden expansion.
  • the area ratio of this third diffusion zone 52 is 1.2, the trailing of the three hollow ribs also having to be taken into account here.
  • the total area ratio of the diffuser is therefore 5.3.
  • both the cylindrical exhaust pipe 22 and the outer boundary wall 14 of the second diffusion zone 51 are welded together on the construction site to form a one-piece element.
  • the second diffusion zone 51 is designed to be insertable axially into the third diffusion zone 52, as is indicated schematically at 23 in FIG. 1.
  • the invention is not limited to the exemplary embodiment shown and described in FIGS. 1 and 2, which has a diffuser with an axial outlet and thus greatly facilitates the arrangement of the flow ribs. It is particularly applicable in particular to steam turbines or gas turbines in general in turbines of exhaust gas turbochargers, and in compressors of gas turbines, which generally all have a so-called axial-radial or axial-radial-axial diffuser.
  • the first diffusion zone 50B here corresponds to that of FIG. 1.
  • the second diffusion zone 51B which is divided into three partial diffusers 17B by means of two guide rings 16B, opens into a third diffusion zone 53B, which deflects strongly with only a slight delay. This strong deflection is greatly favored by the arrangement of the guide rings continuing into the diffusion zone 53B.
  • R is the radius of curvature of the third diffusion zone
  • R 1K is the mean radius of curvature of a single-channel diffusion zone with the same area ratio
  • n is the number of channels.
  • the third diffusion zone 53B opens radially into the chimney 27. The idea of an impact diffuser is also realized in this transition to the chimney.
  • the flow ribs can also be made full instead of hollow.
  • This solution is useful if, for example, an actual exhaust housing is not used, i.e. when the exhaust housing takes over the flow-guiding tasks, i.e. when the outer boundary wall 14 of the diffuser forms the end to the outside and is flanged directly to the turbine housing.
  • FIG. 5 shows how the idea of the invention can be implemented in a compressor diffuser.
  • This could be, for example, the compressor of the gas turbine shown in FIG. 1, it being possible for the system to be equipped with a standing individual combustion chamber (not shown). The latter configuration leads to the almost radial exit from the diffuser shown.
  • both a regular compressor guide row and a follow-up row are provided in the first diffusion zone for swirling the flow. They take over the function of the flow ribs.
  • the compressor guide row acting as the first flow rib 8C is designed according to the above-mentioned criteria, but there is no axial exit from the rib. Because in the flow direction, the rib 8C is followed by a guide line 8'C for further rectification of the flow, which of course can also be designed according to the criteria mentioned.
  • the first diffusion zone extends from the rear edge of the blade 12C to a level behind the guide line 8'C.
  • the two ribs 8C and 8'C could also be combined into a single flow rib.
  • the second diffusion zone is divided into two partial diffusers 17C by a guide ring 16C.
  • This guide ring is held in its position in a third diffusion zone 53C, which is not very delaying but strongly deflects, via ribs 28 on a rotor cover 29C and on the outer boundary wall 14C.
  • the third diffusion zone merges into a fourth diffusion zone 54C, in which deceleration is continued.
  • the shaft part located between the turbine and the compressor is designed as a drum 30.
  • This is surrounded by the already mentioned rotor cover 29C.
  • the annular duct 31C formed between the drum and the rotor cover takes over the guidance of the entire rotor cooling air removed on the hub side between the ribs 8C and 8'C of the compressor to the front side of the turbine, from where it reaches the cooling ducts on the rotor side.
  • This cooling air on the rotor side is combined with the their adherent swirl directed into the ring channel 31C. This ensures on the one hand that the heating of the rotor via the cooling air and thus the level of the transient voltages is as small as possible.
  • the variant of the multi-zone diffuser shown in FIG. 6 is suitable for systems which are equipped with an annular combustion chamber.
  • the available space leads to an almost 180 ° deflection of the diffuser flow.
  • only one compressor guide row is provided, which takes over the function of the flow ribs 8D. They are designed according to the criteria mentioned several times.
  • the rotor-side cooling air is removed from the hub directly at the outlet of the last rotor blades 12D and conducted into the annular duct 31D.
  • the cooling air here has less pressure, but more swirl, provided that the same conditions exist at the outlet of the rotor blades on both compressors.
  • the second diffusion zone is divided into two partial diffusers 17D by a guide ring 16D.
  • This guide ring is held in its position in a third diffusion zone 53D, which is not very slow but strongly deflects, via ribs (not shown) on the rotor cover 29D and on the outer boundary wall 14D.
  • the third diffusion zone merges into a single-channel fourth diffusion zone 54D, in which deceleration continues.
  • the guide ring is made in two parts. In its first section, it consists of a cylindrical sheet metal jacket 16Da, which is held in position on the blade carrier 2D via a plurality of profiled ribs 32 distributed over the circumference. In its second deflecting section 16Db, it consists, for example, of a cast part which is screwed to the first part. To cool the combustion chamber walls, air is branched off from the third diffusion zone via a further annular channel 33.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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EP92113180A 1992-08-03 1992-08-03 Diffuseur à zones multiples pour turbomachine Expired - Lifetime EP0581978B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE59204947T DE59204947D1 (de) 1992-08-03 1992-08-03 Mehrzoniger Diffusor für Turbomaschine
EP92113180A EP0581978B1 (fr) 1992-08-03 1992-08-03 Diffuseur à zones multiples pour turbomachine
US08/098,814 US5338155A (en) 1992-08-03 1993-07-29 Multi-zone diffuser for turbomachine
JP19225493A JP3416210B2 (ja) 1992-08-03 1993-08-03 ターボ装置用の多区域ディフューザ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92113180A EP0581978B1 (fr) 1992-08-03 1992-08-03 Diffuseur à zones multiples pour turbomachine

Publications (2)

Publication Number Publication Date
EP0581978A1 true EP0581978A1 (fr) 1994-02-09
EP0581978B1 EP0581978B1 (fr) 1996-01-03

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EP92113180A Expired - Lifetime EP0581978B1 (fr) 1992-08-03 1992-08-03 Diffuseur à zones multiples pour turbomachine

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US (1) US5338155A (fr)
EP (1) EP0581978B1 (fr)
JP (1) JP3416210B2 (fr)
DE (1) DE59204947D1 (fr)

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EP0690206A2 (fr) 1994-06-29 1996-01-03 ABB Management AG Diffuseur pour une turbomachine
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EP1777420A1 (fr) * 2005-10-20 2007-04-25 Siemens Aktiengesellschaft Diffuseur
DE202010016820U1 (de) 2010-12-21 2012-03-26 Ebm-Papst Mulfingen Gmbh & Co. Kg Diffusor für einen Ventilator sowie Ventilatoranordnung mit einem derartigen Diffusor
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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0690206A3 (fr) * 1994-06-29 1997-08-13 Abb Management Ag Diffuseur pour une turbomachine
EP0690206A2 (fr) 1994-06-29 1996-01-03 ABB Management AG Diffuseur pour une turbomachine
EP1178183A2 (fr) * 2000-07-31 2002-02-06 Alstom (Switzerland) Ltd Turbine à vapeur à basse pression avec un diffuseur à canaux multiples
US6533546B2 (en) 2000-07-31 2003-03-18 Alstom (Switzerland) Ltd. Low-pressure steam turbine with multi-channel diffuser
EP1178183A3 (fr) * 2000-07-31 2003-07-23 ALSTOM (Switzerland) Ltd Turbine à vapeur à basse pression avec un diffuseur à canaux multiples
EP1777420A1 (fr) * 2005-10-20 2007-04-25 Siemens Aktiengesellschaft Diffuseur
US10072671B2 (en) 2010-12-21 2018-09-11 Ebm-Papst Mulfingen Gmbh & Co. Kg Fan diffuser having a circular inlet and a rotationally asymmetrical outlet
DE202010016820U1 (de) 2010-12-21 2012-03-26 Ebm-Papst Mulfingen Gmbh & Co. Kg Diffusor für einen Ventilator sowie Ventilatoranordnung mit einem derartigen Diffusor
WO2012084725A1 (fr) 2010-12-21 2012-06-28 Ebm-Papst Mulfingen Gmbh & Co. Kg Diffuseur de ventilateur à entrée circulaire et sortie sans symétrie de rotation
EP2657482B1 (fr) * 2010-12-24 2019-05-01 Mitsubishi Hitachi Power Systems, Ltd. Structure de trajet d'écoulement et diffuseur d'échappement de turbine à gaz
DE102012016150A1 (de) 2012-08-14 2013-03-07 Daimler Ag Radialverdichter für einen Abgasturbolader
WO2014175763A1 (fr) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Turbomachine et dispositif d'utilisation de chaleur perdue
WO2015022269A1 (fr) 2013-08-16 2015-02-19 Siemens Aktiengesellschaft Conception d'un diffuseur axial prenant en compte des éléments intégrés
EP2837771A1 (fr) * 2013-08-16 2015-02-18 Siemens Aktiengesellschaft Conception d'un diffuseur axial tenant compte d'éléments intégrés
DE102014114798A1 (de) 2014-10-13 2016-04-14 Thermofin Gmbh Axialventilator mit Außen- und Innendiffusor
EP3009682A1 (fr) 2014-10-13 2016-04-20 Thermofin GmbH Ventilateur axial avec diffuseur interne et externe

Also Published As

Publication number Publication date
EP0581978B1 (fr) 1996-01-03
JP3416210B2 (ja) 2003-06-16
JPH06173707A (ja) 1994-06-21
DE59204947D1 (de) 1996-02-15
US5338155A (en) 1994-08-16

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