EP0417433A1 - Turbine axiale - Google Patents

Turbine axiale Download PDF

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Publication number
EP0417433A1
EP0417433A1 EP90113994A EP90113994A EP0417433A1 EP 0417433 A1 EP0417433 A1 EP 0417433A1 EP 90113994 A EP90113994 A EP 90113994A EP 90113994 A EP90113994 A EP 90113994A EP 0417433 A1 EP0417433 A1 EP 0417433A1
Authority
EP
European Patent Office
Prior art keywords
guide vanes
flow
turbine according
blades
ribs
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
EP90113994A
Other languages
German (de)
English (en)
Other versions
EP0417433B1 (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
Publication of EP0417433A1 publication Critical patent/EP0417433A1/fr
Application granted granted Critical
Publication of EP0417433B1 publication Critical patent/EP0417433B1/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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 an axially flow-through turbine, to the outlet rotor blades of which a diffuser is connected, means within the deceleration zone being provided for swirl removal of the swirled flow
  • Such a turbine is known from EP-A 265 633.
  • a rectifying grid is provided within the diffuser, which extends over the entire height of the flowed channel.
  • These means for swirl removal are three flow ribs with thick profiles which are arranged uniformly over the circumference and 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.
  • the diffuser zone between the blading and the flow ribs should therefore 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 on a level in which a relatively low energy level already prevails.
  • 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 , as can be seen from FIG. 2 to be described later (curve A).
  • the pressure behind blading can usually be 0.98 at full load at 40% volume flow rise up to 1.15 bar. This back pressure means that at 40% volume flow, significantly more drive power has to be applied to the machine than if a well-acting diffuser is available.
  • the object of the invention is to design the diffusion zone in axially flow-through turbines of the type mentioned at the outset in such a way that the part-load behavior of the machine is further improved.
  • At least one row with adjustable guide vanes is arranged between the means for swirl removal and the outlet blades.
  • the guide blades have a straight skeleton line with a symmetrical profile.
  • the well-known properties of such grids on insensitivity in the inflow can be used for low-loss deflection.
  • the known gas turbine of which only the last three axially flowed stages are shown in FIG. 1, consists essentially of the bladed rotor 1 'and the blade carrier 2' equipped with guide vanes.
  • the blade carrier is suspended in the turbine housing 3 '.
  • the rotor is in a support bearing 4 ', which in turn is supported in an exhaust housing 5'.
  • This exhaust housing 5 ' consists essentially of a hub-side, inner part 6' and an outer part 7 ', which limit the diffuser 13'.
  • Both elements 6 'and 7' can be one-piece pot housings without an axial parting plane. They are interconnected by several welded supporting flow ribs 8 ', which are arranged evenly distributed over the circumference and whose profile is indicated by 9'. It can be seen that for the reasons mentioned at the outset, the flow ribs 8 'are arranged at a suitable distance from the blading.
  • the pressure recovery C p is plotted on the ordinate, which in a first approximation corresponds to the ratio (p A -p E ) / p * E -p E ), where p A is the static pressure at the outlet of the diffuser, p E is the static pressure at Entry of the diffuser and p * E mean the total pressure at the inlet of the diffuser and thus at the outlet of the blading.
  • Curve A shows the pressure recovery in a diffuser which is equipped with flow ribs which have a pitch to chord ratio of approximately 0.5. It can be seen that the drop is somewhat acceptable up to a c t / c n value, but that the pressure recovery deteriorates dramatically as the volume flow decreases.
  • Curve B shows the completely unreasonable course when flow ribs with a pitch to chord ratio of approximately 1 are used.
  • FIG. 3 The structure of the gas turbine shown there corresponds to that of FIG. 1, which is why the structure is not described again.
  • the same elements as in Fig. 1 are designated in Fig. 3 with the same reference numerals without (').
  • Evenly distributed over the circumference are the same Straightening flow ribs 8 with a straight skeleton line and with a ratio of division to tendon of 0.5. This ratio occurs in the middle section of the flow-through channel of the flow ribs, which run conically in the radial direction.
  • the guide vanes 11 are also symmetrical profiles with a straight skeleton line, as are known for example under the term NACA 0010.
  • these guide blades have a pitch to chord ratio of 0.5 in the middle section of the channel through which the flow passes.
  • Such blades are to a certain extent insensitive to inclined flow, (see article by N. Scholz, "Investigations on blade grids of turbomachines", Journal of Flight Sciences, No. 3, 1955).
  • the guide vanes 11 are tapered in the radial direction and are preferably twisted.
  • the adjustment of the guide vanes 11 in the grating takes place via actuating means, not shown, as are known, for example, from compressor construction.
  • the actual adjustment is preferably carried out automatically as a function of the operating parameters such as load, speed, etc.
  • the greatest pressure recovery is achieved when the guide vanes are adjusted so that the shaft power assumes the greatest possible value under all operating conditions. A permanent performance measurement is therefore suitable.
  • the greatest pressure recovery can also be achieved if the adjustment of the guide vanes takes place in such a way that the static pressure in front of the guide vanes 11, ie behind the outlet rotor blades 12, takes the smallest possible value.
  • a permanent differential pressure measurement p A -p E is therefore suitable.
  • the cylinder section in FIG. 4 shows, on an enlarged scale, the blade plan in the gas turbine zone under consideration.
  • the characters c in each case mean the absolute speed, w the relative speed and u the peripheral speed of the machine.
  • the individual grids have, for example, the following in order to indicate the order of magnitude in an executed example Data:
  • the chord of the guide vanes 11 is 125 mm, that of the flow ribs is approximately 700 mm.
  • the ratio of profile thickness to chord is 0.1 for the guide vanes and for the flow ribs.
  • the flow towards the guide vanes 11 is approximately the same under which they leave the outlet rotor vanes 12, i.e. with the speed c and an angle ⁇ of 60 °.
  • the exhaust gases thus leave the guide vane at an angle of approximately 40 °, with which they strike the front edges of the flow ribs 8, which are also insensitive to oblique flow, where they enter the axial, i.e. be aligned to 0 °.
  • Curve C in FIG. 2 now shows the effect of an optimally adjusted guide blading.
  • the pressure recovery is almost constant and only then drops to a modest extent, compared to the diffuser configuration without guide vanes.
  • the diagram also shows that at full load, ie in the range c t / c n between -0.1 and +0.1 (depending on the design of the blading), the diffuser configurations which are state of the art achieve a somewhat better pressure recovery. This is because the area around which the diffuser flows is less than that with guide vanes.
  • the new measure also makes it possible to allow a certain counter-swirl at the outlet from the last rotor blades 12, since an axial alignment takes place downstream in the diffuser through the guide blades and the flow ribs.
  • This counter-swirl would have the following advantages: - The step work can be increased with constant efficiency; or - The efficiency can be increased with constant step work; - The blades of the last row could be made less twisted, which leads to a reduction in price; - The deflection in the last turbine stage can be reduced, which is particularly important in the case of fluidized-bed-fired gas turbines because of the particle separation.
  • the invention is not limited to the exemplary embodiment shown and described, which relates to a diffuser with an axial outlet and thus greatly facilitates the arrangement of the flow ribs. It is also particularly applicable to steam turbines or the turbines of exhaust gas turbochargers, both of which generally have a so-called axial-radial exit from the blading. In such machines, the means for swirl removal are represented by the radial part of the outlet housing itself.
  • the skeleton shape of the guide vanes can also be curved, which would of course lead to a significant increase in the cost of this additional measure.
EP90113994A 1989-09-12 1990-07-21 Turbine axiale Expired - Lifetime EP0417433B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH332289 1989-09-12
CH3322/89 1989-09-12

Publications (2)

Publication Number Publication Date
EP0417433A1 true EP0417433A1 (fr) 1991-03-20
EP0417433B1 EP0417433B1 (fr) 1993-06-09

Family

ID=4253475

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90113994A Expired - Lifetime EP0417433B1 (fr) 1989-09-12 1990-07-21 Turbine axiale

Country Status (4)

Country Link
US (1) US5102298A (fr)
EP (1) EP0417433B1 (fr)
JP (1) JP3162363B2 (fr)
DE (1) DE59001693D1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0581978A1 (fr) * 1992-08-03 1994-02-09 Asea Brown Boveri Ag Diffuseur à zones multiples pour turbomachine
EP0589215A1 (fr) * 1992-09-25 1994-03-30 Asea Brown Boveri Ag Turbine à gaz avec carter d'échappement et conduit d'échappement
WO1999020874A1 (fr) * 1997-10-17 1999-04-29 Zakrytoe Aktsionernoe Obschestvo 'entek' Conduit d'evacuation pour turbine a vapeur
EP1245784A3 (fr) * 2001-03-30 2009-05-13 General Electric Company Aube de guidage variable
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct
EP3147458A1 (fr) * 2015-09-25 2017-03-29 Siemens Aktiengesellschaft Système basse pression pour une turbine à vapeur et turbine à vapeur

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5279110A (en) * 1992-06-12 1994-01-18 Lin Abraham S Double-rotor rotary engine and turbine
DE4232385A1 (de) * 1992-09-26 1994-03-31 Asea Brown Boveri Gasturbine mit angeflanschtem Abgasgehäuse
JP3070401B2 (ja) * 1994-08-23 2000-07-31 株式会社日立製作所 ガスタービン排気構造
US5494405A (en) * 1995-03-20 1996-02-27 Westinghouse Electric Corporation Method of modifying a steam turbine
JPH11247605A (ja) 1997-12-26 1999-09-14 United Technol Corp <Utc> タ―ボマシ―ンコンポ―ネントの振動緩衝方法及び装置
US6866479B2 (en) * 2003-05-16 2005-03-15 Mitsubishi Heavy Industries, Ltd. Exhaust diffuser for axial-flow turbine
US20050200080A1 (en) * 2004-03-10 2005-09-15 Siemens Westinghouse Power Corporation Seal for a turbine engine
US8757965B2 (en) * 2004-06-01 2014-06-24 Volvo Aero Corporation Gas turbine compression system and compressor structure
US20110176917A1 (en) * 2004-07-02 2011-07-21 Brian Haller Exhaust Gas Diffuser Wall Contouring
US7100358B2 (en) * 2004-07-16 2006-09-05 Pratt & Whitney Canada Corp. Turbine exhaust case and method of making
JP2009531593A (ja) * 2006-03-31 2009-09-03 アルストム テクノロジー リミテッド 流体機械、特に蒸気タービンの案内ブレード
US7731475B2 (en) * 2007-05-17 2010-06-08 Elliott Company Tilted cone diffuser for use with an exhaust system of a turbine
GB201002642D0 (en) * 2010-02-16 2010-03-31 Beachy Head Michael A Engine for thrust and or shaft output
EP2441918A1 (fr) 2010-10-18 2012-04-18 Siemens Aktiengesellschaft Diffuseur annulaire d'une turbine à gaz
US20120198810A1 (en) * 2011-02-04 2012-08-09 General Electric Company, A New York Corporation Strut airfoil design for low solidity exhaust gas diffuser
US9284853B2 (en) * 2011-10-20 2016-03-15 General Electric Company System and method for integrating sections of a turbine
US20140314549A1 (en) * 2013-04-17 2014-10-23 General Electric Company Flow manipulating arrangement for a turbine exhaust diffuser
US11028778B2 (en) 2018-09-27 2021-06-08 Pratt & Whitney Canada Corp. Engine with start assist
US11047314B2 (en) 2019-03-12 2021-06-29 Pratt & Whitney Canada Corp. Systems and methods for control of engine variable geometry mechanism

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2047820A (en) * 1978-11-27 1980-12-03 Kh Polt I Im V I Lenina Exhaust pipe of turbine
US4398865A (en) * 1978-11-10 1983-08-16 Garkusha Anatoly V Exhaust pipe of turbine
EP0265633B1 (fr) * 1986-09-26 1991-02-06 BBC Brown Boveri AG Turbine axiale

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2674845A (en) * 1951-05-02 1954-04-13 Walter D Pouchot Diffuser apparatus with boundary layer control
US2815770A (en) * 1954-05-11 1957-12-10 Westinghouse Electric Corp Diffuser
FR1502832A (fr) * 1966-09-26 1967-11-24 Nord Aviation Hélice carénée à diffusion
DE1925172B2 (de) * 1969-05-17 1977-07-14 Daimler Benz Ag, 7000 Stuttgart Nachleitgitter eines axialverdichters, insbesondere eines ueberschall- axialverdichters
US4116584A (en) * 1973-10-12 1978-09-26 Gutehoffnungshutte Sterkrade Ag Device for extending the working range of axial flow compressors
US4950129A (en) * 1989-02-21 1990-08-21 General Electric Company Variable inlet guide vanes for an axial flow compressor
US4995786A (en) * 1989-09-28 1991-02-26 United Technologies Corporation Dual variable camber compressor stator vane

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4398865A (en) * 1978-11-10 1983-08-16 Garkusha Anatoly V Exhaust pipe of turbine
GB2047820A (en) * 1978-11-27 1980-12-03 Kh Polt I Im V I Lenina Exhaust pipe of turbine
EP0265633B1 (fr) * 1986-09-26 1991-02-06 BBC Brown Boveri AG Turbine axiale

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0581978A1 (fr) * 1992-08-03 1994-02-09 Asea Brown Boveri Ag Diffuseur à zones multiples pour turbomachine
US5338155A (en) * 1992-08-03 1994-08-16 Asea Brown Boveri Ltd. Multi-zone diffuser for turbomachine
EP0589215A1 (fr) * 1992-09-25 1994-03-30 Asea Brown Boveri Ag Turbine à gaz avec carter d'échappement et conduit d'échappement
DE4232088A1 (de) * 1992-09-25 1994-03-31 Asea Brown Boveri Gasturbine mit Abgasgehäuse und Abgaskanal
US5346365A (en) * 1992-09-25 1994-09-13 Asea Brown Boveri Ltd. Gas turbine with exhaust gas casing and exhaust gas duct
WO1999020874A1 (fr) * 1997-10-17 1999-04-29 Zakrytoe Aktsionernoe Obschestvo 'entek' Conduit d'evacuation pour turbine a vapeur
EP1245784A3 (fr) * 2001-03-30 2009-05-13 General Electric Company Aube de guidage variable
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct
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
JP3162363B2 (ja) 2001-04-25
US5102298A (en) 1992-04-07
JPH03100302A (ja) 1991-04-25
DE59001693D1 (de) 1993-07-15
EP0417433B1 (fr) 1993-06-09

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