EP0690206A2 - Diffuseur pour une turbomachine - Google Patents

Diffuseur pour une turbomachine Download PDF

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Publication number
EP0690206A2
EP0690206A2 EP95810378A EP95810378A EP0690206A2 EP 0690206 A2 EP0690206 A2 EP 0690206A2 EP 95810378 A EP95810378 A EP 95810378A EP 95810378 A EP95810378 A EP 95810378A EP 0690206 A2 EP0690206 A2 EP 0690206A2
Authority
EP
European Patent Office
Prior art keywords
diffuser
flow
ribs
channel
rib
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
EP95810378A
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German (de)
English (en)
Other versions
EP0690206B1 (fr
EP0690206A3 (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 Switzerland GmbH
Original Assignee
ABB Management AG
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 Management AG filed Critical ABB Management AG
Publication of EP0690206A2 publication Critical patent/EP0690206A2/fr
Publication of EP0690206A3 publication Critical patent/EP0690206A3/fr
Application granted granted Critical
Publication of EP0690206B1 publication Critical patent/EP0690206B1/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • Such diffusers for turbomachinery are known from EP-B 265 633.
  • a rectifying grid is provided within the diffuser, which extends over the entire height of the channel through which flow passes extends.
  • 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 flowed 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 on large machines 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.
  • the swirling of the flow is to be carried out for the most part, largely without delay.
  • a third subsequent one 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 ct 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 water droplets, are carried in the steam turbines as the return flow sets in, an acute risk of foot erosion can arise on the blades of the last run.
  • the object of the invention is, with a 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, with a swirl-free outflow, the physical to achieve the greatest possible pressure recovery.
  • Axial-radial diffusers are already known from EP-A 581 978, in which the articulation angle idea is realized.
  • these are multi-zone gas turbine diffusers, as shown in FIG. 4 there.
  • a first single-channel diffusion zone has a bell shape here.
  • a second diffusion zone which is divided into three partial diffusers by means of two guide rings, opens into a third diffusion zone, which deflects strongly with only a slight delay. This strong deflection is greatly promoted by the arrangement of the guide rings continuing into the diffusion zone. This measure brings about a favorable increase in the mean radius of curvature of the third diffusion zone based on the channel height.
  • the present invention starting from a system in which there is a strongly divergent flow at the exit of a blading, with counter-swirl at the hub, co-swirl at the cylinder and significantly higher flow energy in the radially outer zone, has the advantage, for the first time, of the articulation angle idea, the The aim of achieving the lowest possible total pressure inhomogeneity over the blade height is to be used successfully with a two-channel diffuser with axial / radial deflection.
  • the guide plate with the inner and outer flow ribs and the associated inner and outer diffuser rings are designed as self-supporting half-shells with a horizontal parting plane, the mechanical integrity of the guide plate achieved in this way facilitates simple assembly / disassembly of the diffuser and access to the blading.
  • the ratio of the rib spacing a from the exit of the blading 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 diverted free of detachment in the swirl-free outflow direction and that a contribution is made to the desired deceleration.
  • 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 advantageous with regard to a shock-free entry and an axial one Outflow selected. This guarantees the desired high pressure recovery as well as a certain insensitivity to partial load.
  • the radial flow ribs are provided at their two ends with base plates with which they are vane-shaped in the blade carrier and in the guide plate. It is particularly favorable if both base plates are provided on their arcuate circumferential surfaces with ring grooves, in which spikes of the twists engage.
  • tensile forces can also be introduced into the guide vane carrier via the flow ribs. In the event of an erosive attack on the flow ribs, these can be exchanged in the simplest way.
  • the direction of flow of the working fluid is indicated by arrows.
  • the main components are the outer housing 1, the inner housing 2 and the rotor 3.
  • the outer housing consists of several parts, not specified, which are usually screwed or welded together only at the place of installation.
  • the inner housing consists of the inflow housing 4 in the form of a torus and the downstream guide blade carriers 5, which are equipped with the guide blades 6.
  • the outer casing, inner casing and blade carrier are divided horizontally and screwed together on separating flanges 41 (FIG. 3). In the plane of these separating flanges, the inner housing is supported in the outer housing by means of support arms.
  • the rotor 3 equipped with the rotor blades 7 is welded together from shaft washers and shaft ends with integrated coupling flanges. It is supported in bearing housings by means of plain bearings, not shown.
  • the path of the steam leads from an additional steam line via the steam duct in the outer casing 1 into the inner casing 2.
  • the torus ensures that the steam is well guided to the both floods of blading reached.
  • the steam passes through an annular diffuser 11 into the evaporation chamber 30 of the outer housing 1 before it flows downward (in the drawing) to the condenser.
  • Axial flow through shaft seals 13 on the rotor bushing in the outer housing prevent air from entering the exhaust steam.
  • the articulation angle idea has not been realized here.
  • the opening angle of the blading is greatly reduced at the diffuser inlet. For only local support of the deflection, two axially staggered guide plates can be seen, which must be attached to the diffuser inner walls and outer walls with the above-mentioned disadvantageous struts.
  • the flow-limiting outer walls of the diffuser are formed by the diffuser outer ring 25 and the diffuser inner ring 24.
  • the former is screwed to the blade carrier 3 (as indicated).
  • the latter is made up of several parts.
  • the closest to the blading is an annular part 24A which extends at least approximately in the axial direction. This is followed by a deflecting ring part 24B, which merges into an even more diverting ring part 24C. Parts 24A and 24B are welded together. Axial play is provided between parts 24B and 24C.
  • the housing of the shaft seal 13 is fastened to the ring part 24C. Downstream, the ring part 24C is connected to the rear, substantially perpendicular baffle 31 by a flange. The baffle is in turn connected to the outer housing 1 in a vapor-tight manner.
  • the diffuser is divided into two sub-channels by means of a deflecting baffle 60, an inner channel 50 and an outer channel 51.
  • this baffle is likewise made in three parts; a first part 60A, a strongly deflecting middle part 60B and a vertically extending part 60C. The three parts are welded together as a whole.
  • the area ratios of the two subchannels 50, 51 are determined taking into account the total pressure profile or the flow energies behind the last moving blade 7A.
  • a larger area ratio is selected if, for example, large kinetic energies have to be implemented, which can be the case in the outer channel; accordingly, a smaller area is selected for the inner channel if smaller energies are to be implemented there.
  • the same surfaces are provided for the outer channel 50 and the inner channel 51, namely from the diffuser inlet to the diffuser outlet. This gives the different angles of attack for the guide plate part 60B and the diffuser inner ring 24B, 24C.
  • the guide plate part 60A is set so that the flow flows smoothly.
  • the inner diffuser ring 24 and the guide plate 60 can also be designed with a constant curvature.
  • the decisive factor for the desired functioning of the diffuser is now the kink angle of its two boundary walls 24 and 25 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 7A.
  • the channel contour on the blade root is cylindrical, that on the blade tip runs obliquely at an angle of up to 40 °.
  • the mentioned angle of 40 ° would be completely unsuitable 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 40 ° to approx. 7 °.
  • the diffuser is therefore designed solely on the basis of fluid dynamics. The considerations must lead to a homogeneous total pressure profile over the entire duct height. The two bending angles are therefore determined on the basis of the entire flow in the blading and in the diffuser.
  • the kink angle ⁇ N is realized on the hub by means of a collar 80 arranged in a suitable manner on the rotor 3.
  • the kink angle extends over the axial length of the first diffuser ring 24A to which the flow is flowing.
  • An oblique annular channel 81 is formed between the collar end and the inner diffuser ring 24A.
  • the underside of the collar and the front edge of the diffuser inner ring 24A are configured accordingly. This measure has the advantage of shielding the outflow in the blade root area from harmful cross-flow effects.
  • Such cross flows are driven in the state-of-the-art machines by the pumping action of the rotor side wall 32, the sealing steam, and the rotational asymmetry of the outer housing 1.
  • the channel is therefore divided in the radial direction by means of flow-conducting guide rings into a plurality of partial diffusers which are dimensioned according to the known rules for a straight diffuser.
  • the only guide plate 60 already described is provided, which divides the flow-through channel into two partial diffusers.
  • the flow-carrying parts of this diffusion zone are shown in Fig. 2.
  • the two partial diffusers are designed as bell-shaped diffusers. This means that the equivalent opening angle ⁇ of the meridian contours downstream of the kink angles ⁇ Z and ⁇ N determined according to the above criteria is reduced in order to avoid flow separation. This happens first to a greater extent and then to a lesser extent, which leads to a shape equivalent to the bell shape.
  • flow ribs 70 through which radial flow flows are now arranged in the outer channel 51 of the diffuser and flow ribs 71 through which flow flows diagonally in the inner channel 50.
  • FIG. 2 shows that the inner flow ribs 71 are connected to the diffuser inner ring 24B and to the front guide plate part 60A, for example by welding. It is also shown how the radially flow-through flow ribs 71 are fastened in the outer channel 51. Shown is a suspension variant that is suitable for absorbing both tensile and compressive forces.
  • the same foot plates 14 are provided on both sides of the flow ribs, which are guided in the known manner of hammer head type or dovetail type in corresponding rotations of the diffuser outer ring 25 and the vertically extending part 60C of the guide plate.
  • the arcuate circumferential surfaces of both the inner and the outer sides of the plate are provided with grooves, in which correspondingly sized serrations of the recess 15 engage.
  • the baffle system 60 A, B, C forms a self-supporting unit with the inner and outer flow ribs 71, 70 and the associated inner (24A, B) and outer (25) diffuser rings.
  • these units are designed as half-shells with a horizontal parting plane. These half-shells are screwed together in the parting plane via inner flanges 26 (FIG. 3). The parting plane 26 lies at the level of the machine axis.
  • the lower half-shell (not shown) can be attached to the housing of the shaft seal 13.
  • This training facilitates access to the blading. If, for example, an end blade 7A is to be removed, the following procedure is followed: First of all, the evaporation hood (part of the outer housing 1) together with the upper housing of the Shaft seal 13 lifted off. Then, after loosening the flange screws of the diffuser inner ring and screwing the diffuser outer ring, the upper half-shell of the self-supporting structural unit as a whole can be lifted off.
  • such a diffuser insert is particularly suitable for retrofitting existing systems.
  • the required diffuser geometry - which includes the kink angle, the area ratios of the subchannels and the geometry of the flow ribs - it is advisable to measure the flow beforehand immediately after the last row 7A.
  • the required diffuser geometry is then determined according to the inverse design principles.
  • the diffuser insert should be designed on the basis of the guarantee points or the relevant operating range.
  • the number of radially flowed through outer flow ribs 70 is fifty (50) pieces in the present case. According to FIG. 3, this even number has the advantage that there are no ribs in the horizontal parting plane.
  • the large number of flow ribs 70 is also advantageous, inter alia, because this results in a low radial height or a small influence on the space for diffuser and exhaust steam.
  • the number of inner flow ribs 71 in the present case is eighteen (18) pieces. 3 shows, even with this even number, there are no ribs in the horizontal parting plane. This number and the fluidic design of the ribs 70, 71 are now based on the following considerations:
  • the distance a between the front edge 72 of the inner flow ribs 71 and the exit of the blading is related for rib division t - which measure is for the number of ribs - set. If this ratio is at least 0.5, interference with the last row 7A of the blading can be largely avoided.
  • the flow ribs have a supporting function, so a minimum cross-section should not be undercut.
  • a minimum chord length should also not be undercut. If the ratio of the rib chord s to the rib pitch t is at least 1 and the ratio of the maximum profile thickness d max of the flow ribs to the chord s to be described later is approximately 0.15, both tasks can be performed.
  • the diffusion zone is provided with a horizontal parting plane, i.e. the inner diffuser ring, the outer diffuser ring and the baffle are split.
  • 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 number of ribs best suited for this purpose is 18.
  • 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 selected with regard to a smooth entry and an axial outflow, which generally leads to a variable curvature above the height of the ribs.
  • the diagonally flowed through inner ribs 71 can have a basic conicity. This is based on the idea of a ratio of tendon to division (s / t) adapted to the redirection task. This configuration forms the starting position, which is then adapted to the actual flow in sections above the height of the ribs.
  • the front edges 72 of the ribs are oriented above the rib height in such a way that they are cut perpendicularly by the streamlines. This leads to leading edges, which in no way have to be aligned radially or axially.
  • the new diffuser insert has great efficiency potential; pressure recovery coefficients of up to 60% are possible.
  • the kink angle idea together with the flow-oriented ribs for low-loss conversion of the swirl energy into pressure energy and the swirl-free outflow of the two rows of ribs ensures a minimum of residual energy.
  • the existing symmetrical flow spaces in the exhaust steam, and especially in the parting plane, are used as best as possible with regard to the lowest possible speed level.
  • the inner channel 50 is only partially required for the actual diffusion process.
  • the downstream part in the region of the baffle 31 increases the free cross section in the parting plane and thus serves to reduce the harmful rotational asymmetry.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP95810378A 1994-06-29 1995-06-08 Diffuseur pour une turbomachine Expired - Lifetime EP0690206B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4422700A DE4422700A1 (de) 1994-06-29 1994-06-29 Diffusor für Turbomaschine
DE4422700 1994-06-29

Publications (3)

Publication Number Publication Date
EP0690206A2 true EP0690206A2 (fr) 1996-01-03
EP0690206A3 EP0690206A3 (fr) 1997-08-13
EP0690206B1 EP0690206B1 (fr) 2000-03-01

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EP95810378A Expired - Lifetime EP0690206B1 (fr) 1994-06-29 1995-06-08 Diffuseur pour une turbomachine

Country Status (5)

Country Link
US (2) US5588799A (fr)
EP (1) EP0690206B1 (fr)
JP (1) JPH0842306A (fr)
CN (1) CN1116271A (fr)
DE (2) DE4422700A1 (fr)

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EP3147458A1 (fr) * 2015-09-25 2017-03-29 Siemens Aktiengesellschaft Système basse pression pour une turbine à vapeur et turbine à vapeur

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JP6012222B2 (ja) 2012-03-30 2016-10-25 三菱重工業株式会社 静翼セグメント、これを備える軸流流体機械及びその静翼連結方法
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CN105065068B (zh) * 2015-08-13 2016-07-20 德阳东汽电站机械制造有限公司 一种用于汽轮机排汽缸的导流环
US10287920B2 (en) 2015-11-24 2019-05-14 General Electric Company System of supporting 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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JP7254472B2 (ja) * 2018-09-28 2023-04-10 三菱重工業株式会社 蒸気タービンの排気室、蒸気タービン及び蒸気タービンの換装方法
CN113123838B (zh) * 2019-12-30 2023-05-30 上海汽轮机厂有限公司 一种排汽缸及其应用的汽轮机
JP7368260B2 (ja) 2020-01-31 2023-10-24 三菱重工業株式会社 タービン
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EP0581978A1 (fr) 1992-08-03 1994-02-09 Asea Brown Boveri Ag Diffuseur à zones multiples pour turbomachine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2295732A1 (fr) * 2009-09-14 2011-03-16 Alstom Technology Ltd Turbine axiale et procédé de décharge d'un écoulement d'une turbine axiale
US8506233B2 (en) 2009-09-14 2013-08-13 Alstom Technology Ltd. Axial turbine and method for discharging a flow from an axial turbine
DE102010044819B4 (de) 2009-09-14 2022-12-15 General Electric Technology Gmbh Axialturbine und ein Verfahren zum Abführen eines Stroms von einer Axialturbine
EP3147458A1 (fr) * 2015-09-25 2017-03-29 Siemens Aktiengesellschaft Système basse pression pour une turbine à vapeur et turbine à vapeur

Also Published As

Publication number Publication date
EP0690206B1 (fr) 2000-03-01
DE4422700A1 (de) 1996-01-04
JPH0842306A (ja) 1996-02-13
US5707208A (en) 1998-01-13
DE59507868D1 (de) 2000-04-06
US5588799A (en) 1996-12-31
CN1116271A (zh) 1996-02-07
EP0690206A3 (fr) 1997-08-13

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