EP2824287B1 - Druckgehäuse einer Turbomaschine - Google Patents

Druckgehäuse einer Turbomaschine Download PDF

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Publication number
EP2824287B1
EP2824287B1 EP13175613.2A EP13175613A EP2824287B1 EP 2824287 B1 EP2824287 B1 EP 2824287B1 EP 13175613 A EP13175613 A EP 13175613A EP 2824287 B1 EP2824287 B1 EP 2824287B1
Authority
EP
European Patent Office
Prior art keywords
heat transfer
transfer medium
casing
flange
hole
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.)
Active
Application number
EP13175613.2A
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English (en)
French (fr)
Other versions
EP2824287A1 (de
Inventor
Armin Busekros
Robert Przybyl
Gregory Jeunet-Mancy
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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 Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Priority to EP13175613.2A priority Critical patent/EP2824287B1/de
Priority to US14/317,643 priority patent/US20150010389A1/en
Priority to CN201410322141.5A priority patent/CN104279189A/zh
Publication of EP2824287A1 publication Critical patent/EP2824287A1/de
Application granted granted Critical
Publication of EP2824287B1 publication Critical patent/EP2824287B1/de
Active 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements

Definitions

  • the present invention relates to the field of thermal turbomachines, such as stationary turbines for power generation. It refers to a pressure casing, devided in at least two casing shells which are removably connected in a pressure-tight manner in a parting plane by means of a flange.
  • the published patent application DE 10225260 A1 discloses a casing for an axial turbomachine with an upper half shell and a lower half shell connected in a horizontal parting plane by means of a flange.
  • the connecting bolts extend through a through hole in the upper half shell and are being placed in a thread hole of the lower half shell, whereby an annular space is formed between the outer surface of the bolt and the inner surface of the through hole.
  • a thermally insulated sleeve is located in an upper part of this annular space. It is the aim of this solution to minimize the heat transfer between the connecting bolts and the ambient fluid. This solution cannot solve the above-mentioned problems during the warm-up phase.
  • Patent application WO 2003078799 A1 discloses an arrangement for cooling or heating of the flange bolts in a turbine casing.
  • a bolt comprises one or more bore holes extending axially through the bolt. Said bore holes are optionally charged either with a heating or with a cooling medium. The cooling or heating medium flows through the at least one bore hole thereby cooling or heating the bolt.
  • the stabilized temperature regime of the bolt effects a damping of bolt relaxation and ensures that the bolting forces remain stable during steady-state operation and during transient operations.
  • Another disclosed embodiment teaches to equip the bolts with additional radial bore holes extending from the axial bore hole to the annular space between the bolt and the flange boring. This embodiment effects an increase of heat transfer and forces the cooling or heating gradient. It is a disadvantage of this solution that the plurality of bore holes weakens the mechanical integrity of the bolts. This weakening of integrity has to be compensated by an undesirably larger dimensioning of the bolts.
  • JP S61 200310 A describes a pressure casing cpmprising a flange sealingly pressed together by threaded bolts.
  • the connecting bolts extend through a through hole in the upper half shell and are being placed in a thread hole of the lower half shell, whereby an annular space is formed between the outer surface of the bolt and the inner surface of the through hole.
  • a cooling or heating fluid is introduced and exits the annular space at the lower end.
  • US 6 352 404 B1 discloses a casing having shells joined at a parting plane and proivided with respective flanges sealingly clamped by bolts extending trough the flanges prependicularly to the parting plane. Channels for a heat transfer fluid for transferring heat to/from the bolts are arranged in the parting plane of the flanges.
  • a hollwo bolt is known that is elongated by filling it with a pressurized fluid to a certain extend. Once the ciorrect elongation has been achiecved a nut is fastened and the pressure of the fluid is released.
  • the object is achieved by a pressure casing as set forth in claim 1.
  • the invention is based on a pressure casing which comprises at least two casing shells which can be connected in a pressure-tight manner in a parting plane by means of a flange, wherein the casing shells are pressed together with sealing effect in the parting plane in the region of the flange by means of at least one threaded bolt which extends through the flange perpendicularly to the parting plane.
  • the invention is distinguished by the fact that the at least one threaded bolt is charged by a heat transfer medium, i.e.
  • this heat transfer medium is supplied or discharged via passages and at least a portion of the passages (22, 23, 24) for the heat transfer medium are arranged in the parting plane (11) of the flange (12) .
  • This measure supports an equalization of the temperatures of the flange and the connecting bolts, thereby avoiding overload of the bolts during start up phases and diminishment of bolting forces during shutdown.
  • the heat transfer medium charges the bolt in the annular space between the shaft of the bolt and the inner lateral surface of the through hole.
  • annular space between the shaft of the bolt and the inner lateral surface of the through hole is sealed in a gas tight manner on its both longitudinal ends, wherein at the one end a feed hole for the heat transfer medium leads into the annular space and at the opposite end an outlet hole for the heat transfer medium branches off.
  • One development of the invention is characterized in that the heat transfer medium is air.
  • the heat transfer medium is compressor air.
  • the heat transfer medium is steam, particularly branched off steam from a steam turbine.
  • the pressure casing 10 comprises, as shown in Fig. 1 , an upper casing shell 10a and a lower casing shell 10b which abut on a flange 12 in a parting plane 11 and are bolted to each other there in a pressure-tight manner by threaded bolts 14.
  • each of the threaded bolts 14 provision is made in the upper casing shell 10a in the region of the flange 12 for a through-hole 13 with an inner diameter larger than the outer diameter of the bolt 14 to provide an annular space 17, and provision is made in the lateral surface of this through hole 13 for a supply and discharge of either a heating or a cooling medium. On both sides the annular space 17 is sealed in a gas tight manner.
  • either a cooling or a heating medium is supplied from a source 20 to the annular space 17 via at least one feed hole 22.
  • the feed hole 22 opens into the space 17 at one of its longitudinal ends. From there the heat transfer medium flows around the shaft of the bolt 14 towards the opposite end of space 17.
  • the heat transfer medium leaves the annular space 17 to be discharged in a volume 21 with a lower pressure compared to the pressure of the source 20.
  • This volume 21 may be a suitable cavity inside or outside of the casing 10.
  • Outlet hole 23 again extends through the flange 12 in a way to intensify the heat transfer between the heat transfer medium and the flange 12.
  • the heat transfer medium is supplied from a fluid source 20.
  • Source 20 for the heat transfer medium is an air plenum of a gas turbine. From this source 20 the feed hole 22 is passed through the flange 12 in a way to allow heat transfer between the flange 12 and the heat transfer medium.
  • the feed hole 22 may have a circular or a non-circular, particularly a rectangular cross section.
  • the feed hole 22 may comprise a section with an enlargement of cross section to combine feed holes 22 from different sources 20 or to branch feed holes 22 to different through holes 13.
  • the feed holes 22 or the outlet holes 23 are arranged in the parting plane 11.
  • curved or even serpentine holes 22, 23 can be manufactured easily, e.g. by milling a groove in the contact surfaces of the flange 12.
  • Fig. 2 schematically shows alternative embodiments to realize this invention.
  • a mass flow of air is discharged into feed line 22.
  • Feed line 22 passes an area of the flange 12 and ends in the through hole 13' of a first threaded bolt 14'.
  • the heat transfer medium passes through a connecting hole 24 inside of flange 12 to a second bolt 14" in a second through hole 13" etc.
  • the exhaust heat transfer medium 26 is discharged via outlet hole 23 into the flow channel 18.
  • the flow channel 18 of the turbomachine serves as source of the heat transfer medium.
  • a partial flow of the working medium is branched off from the flow channel 18 and fed into the feed line 22.
  • the heat transfer medium is passed through the flange 12 to one or more connecting bolts 14 and is finally discharged via the outlet hole 23 into a cavity 21 inside or outside of the outer casing of the turbomachine.
  • Fig. 3 refers to an example which is not part of the invention, especially applicable to a compressor casing.
  • the lower and the upper shell of the compressor are equipped with a flange 12.
  • the flow channel 18 of the compressor comprises a number of compressor stages.
  • a feed line 22 branches off from the flow channel 18 at a defined vane row (i) (reference 28).
  • the feed line 22 extends through the flange 12 and ends inside a first through hole 13' at its longitudinal end.
  • a connecting hole 24 connects this first through hole 13' with a second through hole 13", whereby this second hole 13" is located upstream against the flow direction 19 of the working medium in the flow channel 18.
  • an outlet hole 23 extends through the flange 12 and ends in the flow channel 18 at a vane row 29 upstream of the above-mentioned vane row (i) (reference 29), i.e. in an upstream compressor section with a lower pressure.
  • a partial flow 25 of the compressor air stream is branched off from the flow channel 18 into the feed hole 22.
  • the air stream 25 passes the flange 12, enters the annular space 17' between the through hole 13' and the shaft of the first bolt 14' at its e.g. upper longitudinal end.
  • the air flows along the shaft of bolt 14' under convective heat transfer.
  • the air flow 27 enters the connecting hole 24, passes again the flange 12 and reaches the through hole 13" of the second bolt 14", flows along the shaft of the second bolt 14".
  • the exhausted air 26 is directed back into the flow channel 18 at a vane row 29, located upstream of the vane row 28.
  • This embodiment of a device for flange and bolts temperature adjustment uses the pressure difference between two different compressor stages.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (11)

  1. Druckgehäuse einer Turbomaschine, das mindestens zwei Gehäuseschalen (10a, 10b) aufweist, die in druckdichter Weise in einer Trennebene (11) mittels eines Flansches (12) verbunden sind, wobei die Gehäuseschalen (10a, 10b) in der Trennebene (11) im Bereich des Flansches (12) mittels mindestens eines Gewindebolzens (14), der durch eine Durchgangsbohrung (13) in dem Flansch (12) senkrecht zu der Trennebene (11) verläuft, mit abdichtender Wirkung zusammengepresst werden, wobei der mindestens eine Gewindebolzen (14) mit einem Wärmeübertragungsmedium beschickt wird, wobei mindestens eines der Zuführlöcher (22) oder Auslasslöcher (23) für das Wärmeübertragungsmedium in der Trennebene (11) des Flansches (12) angeordnet ist, dadurch gekennzeichnet, dass:
    die Zuführlöcher (22) das Wärmeübertragungsmedium aus einem Vorrat erhalten und die Auslasslöcher (23) in einen Durchflusskanal (18) für ein Arbeitsmedium innerhalb des Druckgehäuses ableiten; oder
    die Zuführlöcher (22) das Wärmeübertragungsmedium aus dem Durchflusskanal (18) erhalten und die Auslasslöcher (23) in einen Hohlraum (21) außerhalb des Druckgehäuses ableiten.
  2. Druckgehäuse nach Anspruch 1, dadurch gekennzeichnet, dass ein oder mehrere Zuführlöcher (22) für das Wärmeübertragungsmedium an einer Quelle (20) für das Wärmeübertragungsmedium beginnen, durch den Flansch (12) verlaufen und in einer seitlichen Oberfläche des Durchgangslochs (13) enden.
  3. Druckgehäuse nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass ein oder mehrere Auslasslöcher (23) für das Wärmeübertragungsmedium an dem Durchgangsloch (13) beginnen, durch den Flansch (12) verlaufen und in einem Volumen (21) mit einem im Vergleich zu dem Druck der Quelle (20) relativ niedrigem Druck enden.
  4. Druckgehäuse nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass ein ringförmige Raum (17) zwischen der inneren Seitenfläche des Durchgangslochs (13) und dem Schaft des Gewindebolzens (14) vorgesehen ist, dieser ringförmige Raum (17) in dichter Weise an seinen beiden Längsenden abgedichtet ist und dieser ringförmige Raum (17) mit dem Wärmeübertragungsmedium beschickt wird.
  5. Druckgehäuse nach Anspruch 4, dadurch gekennzeichnet, dass mindestens eines der Zuführlöcher (22) oder der Auslasslöcher (23) sich in den ringförmigen Raum (17) öffnet.
  6. Druckgehäuse nach Anspruch 5, dadurch gekennzeichnet, dass das mindestens eine Zuführloch (22) und das mindestens eine Auslassloch (23) zu entgegengesetzten Enden des ringförmigen Raums (17) führen.
  7. Druckgehäuse nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet das mindestens eines der Zuführlöcher (22) oder Auslasslöcher (23) für das Wärmeübertragungsmedium durch den Flansch (12) geführt ist.
  8. Druckgehäuse nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass das Wärmeübertragungsmedium Luft ist.
  9. Druckgehäuse nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass das Wärmeübertragungsmedium Dampf ist.
  10. Druckgehäuse nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Turbomaschine ein Verdichter ist.
  11. Druckgehäuse nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass das Gehäuse ein innerer Träger einer Gasturbine ist.
EP13175613.2A 2013-07-08 2013-07-08 Druckgehäuse einer Turbomaschine Active EP2824287B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13175613.2A EP2824287B1 (de) 2013-07-08 2013-07-08 Druckgehäuse einer Turbomaschine
US14/317,643 US20150010389A1 (en) 2013-07-08 2014-06-27 Pressure casing of a turbomachine
CN201410322141.5A CN104279189A (zh) 2013-07-08 2014-07-08 涡轮机的压力机壳

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13175613.2A EP2824287B1 (de) 2013-07-08 2013-07-08 Druckgehäuse einer Turbomaschine

Publications (2)

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EP2824287A1 EP2824287A1 (de) 2015-01-14
EP2824287B1 true EP2824287B1 (de) 2020-05-13

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EP13175613.2A Active EP2824287B1 (de) 2013-07-08 2013-07-08 Druckgehäuse einer Turbomaschine

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US (1) US20150010389A1 (de)
EP (1) EP2824287B1 (de)
CN (1) CN104279189A (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108521574A (zh) * 2012-09-28 2018-09-11 索尼公司 编码设备、编码方法、解码设备和解码方法
FR3019210B1 (fr) * 2014-04-01 2016-05-13 Snecma Partie de turbomachine comportant une bride avec un dispositif de drainage
CN105507963A (zh) * 2015-12-23 2016-04-20 上海电气电站设备有限公司 用于冷却在高温下工作的螺栓的冷却系统
FR3049003B1 (fr) * 2016-03-21 2018-04-06 Safran Aircraft Engines Ensemble d'anneau de turbine sans jeu de montage a froid
US11111821B2 (en) * 2019-09-18 2021-09-07 Raytheon Technologies Corporation Retention assembly for gas turbine engine

Citations (1)

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Publication number Priority date Publication date Assignee Title
US6352404B1 (en) * 2000-02-18 2002-03-05 General Electric Company Thermal control passages for horizontal split-line flanges of gas turbine engine casings

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JPS6018803B2 (ja) * 1977-12-05 1985-05-13 株式会社日立製作所 タ−ビン用ケ−シング
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JPS58206811A (ja) * 1982-05-28 1983-12-02 Toshiba Corp 蒸気タ−ビンケ−シング
JPS5979011A (ja) * 1982-10-27 1984-05-08 Hitachi Ltd 蒸気タ−ビンのボルトク−リング法
JPS61200310A (ja) * 1985-03-01 1986-09-04 Fuji Electric Co Ltd 蒸気タ−ビンのフランジおよび締付ボルトの温度加減方法
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JP4015284B2 (ja) * 1998-06-09 2007-11-28 三菱重工業株式会社 蒸気タービンケーシングのフランジ冷却構造
DE10225260A1 (de) 2001-09-07 2003-03-27 Alstom Switzerland Ltd Fügeverband
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Publication number Publication date
CN104279189A (zh) 2015-01-14
EP2824287A1 (de) 2015-01-14
US20150010389A1 (en) 2015-01-08

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