EP3715590A1 - Turbomaschinengehäuseanordnung - Google Patents

Turbomaschinengehäuseanordnung Download PDF

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Publication number
EP3715590A1
EP3715590A1 EP19165437.5A EP19165437A EP3715590A1 EP 3715590 A1 EP3715590 A1 EP 3715590A1 EP 19165437 A EP19165437 A EP 19165437A EP 3715590 A1 EP3715590 A1 EP 3715590A1
Authority
EP
European Patent Office
Prior art keywords
turbine housing
pin
turbine
housing
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.)
Withdrawn
Application number
EP19165437.5A
Other languages
English (en)
French (fr)
Inventor
Milan Korista
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP19165437.5A priority Critical patent/EP3715590A1/de
Publication of EP3715590A1 publication Critical patent/EP3715590A1/de
Withdrawn legal-status Critical Current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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention is related to a turbomachinery housing assembly comprising a first turbine housing, wherein the first turbine housing has a first turbine housing upper part and a first turbine housing lower part and the first turbine housing upper part and the first turbine housing lower part are joined together at an longitudinal split plain and a second turbine housing, wherein the second turbine housing has a second turbine housing upper part and a second turbine housing lower part and the second turbine housing upper part and the second turbine housing lower part are joined together at an longitudinal split plain, wherein the first turbine housing and the second turbine housing are joined together in longitudinal direction at a circumferential split plain, in that way, that plains of longitudinal split and circumferential split intersect at line, wherein this intersection line is line of so called cross-joint-line.
  • Multistage turbomachinery housings are usually consisting of at the minimum two housings, a first housing (higher pressure housing) and a second housing (lower pressure housing). Inside the housings a rotor is rotatable mounted. For mounting the rotor inside the housing the turbine housings the turbine housings has turbine housing upper parts and a turbine housing lower parts and the turbine housing upper parts and the turbine housing lower parts are joined together at longitudinal split plain. The first turbine housing and the second turbine housing are joined together in longitudinal direction at a circumferential split plain. The plains of longitudinal split and circumferential split intersect at line, wherein this intersection line is line of so called cross-joint-line.
  • the cross-joint let mutually mechanically interact 4 elements (parts of turbine housings) at the region alongside the cross-joint-line where all four edges of all 4 housing parts stick to each other. Due to this concentration of the mechanical interactions at very limited area, theoretically just at the cross-joint-line, material of the flanges are heavily loaded and the shape of these machined parts can be deformed. This can result in cross joint leakage or the leakage next to that area in general.
  • turbomachinery housing according to independent claim 1. Further features and details of the present invention result from the sub claims, the description and the drawings.
  • a turbomachinery housing assembly comprising a first turbine housing, wherein the first turbine housing has a first turbine housing upper part and a first turbine housing lower part and the first turbine housing upper part and the first turbine housing lower part are joined together at an longitudinal split plain, a second turbine housing, wherein the second turbine housing has a second turbine housing upper part and a second turbine housing lower part and the second turbine housing upper part and the second turbine housing lower part are joined together at an longitudinal split plain, wherein the first turbine housing and the second turbine housing are joined together in longitudinal direction at a circumferential split plain, in that way that plains of longitudinal split and circumferential split intersect at line, wherein this intersection line is line of so called cross-joint-line.
  • a hole is drilled, which is formed and arranged in a manner, so that there is no common contact of all four turbine housing parts (first turbine housing upper part, first turbine housing lower part, second turbine housing upper part, second turbine housing lower part) when these parts are assembled together, so that connected turbine housing parts can mechanically interact to adjacent parts only.
  • the drilled hole is closed by a pin.
  • This pin is pre-stressed by elastic and/or plastic deformation to create big enough contact pressure to keep the contact tight. This pre-stressing can be done by expanding the hollow pin in the same way as heat exchanger tubes or any other means.
  • turbomachinery housing assembly mechanical interactions between the 4 housing parts will be reduced as much as possible. This is achieved by a hole which leads to that no cross-joint-line is exist let mutually interact only 2 neighbouring housing parts. The hole is closed by a pin which seals the turbomachinery housing.
  • An embodiment of the invention provides that the drilling axis of the hole is radial to a turbine axis. This facilitates the alignment of the drill and ensures that the cross-joint-line will be removed completely.
  • a further embodiment of the invention provides that the hole and the pin have a cylindrical or conical outer shape.
  • the cylindrical or conical shape is easy and precisely to manufacturing.
  • the hole and the pin could be adapted easily to each other.
  • the hole shall be preferably pre-machined. That disconnects mutual interactions of diagonally connect housing parts during the assembly.
  • the final shape of the hole shall be preferably drilled or even any other way fine machined after the cross joint is assembled. It shall also be enough material around the hole to allow re-machining the hole when the turbomachinery housing is opened for revision, repairs or other.
  • a further embodiment of the invention provides that the pin is a hollow caped pin.
  • the pin should be flexible enough to disconnect contact areas of housing parts which are not adjacent. The flexibility could be reached by a hollow pin which is more flexible than a rod.
  • a further advantage of a hollow caped pin is, that it allows using a tube expanding tool to increase the pin pre stressing or pre straining after the pin is put in the hole (using tube expanding tools for condenser tubes for instance). By pre-stressing or pre-straining of the pin the contact pressure to tight the pin in the hole will be increases so that the pin stays in the hole due to the friction force also under pressure.
  • Fig. 1 shows schematically a sectional view of an inventive turbomachinery housing assembly.
  • the turbomachinery housing assembly comprising a first turbine housing 1, (for example a low pressure steam turbine housing) and a second turbine housing 2 (for example an exhaust steam turbine housing).
  • first turbine housing 1 for example a low pressure steam turbine housing
  • second turbine housing 2 for example an exhaust steam turbine housing
  • each of the turbine houses 1, 2 are divided in a housing upper part and a housing lower part.
  • the first turbine housing 1 has a first turbine upper part 1' and a first turbine housing lower part 1"
  • the second turbine housing 2 has a second turbine upper part 2' and a second turbine housing lower part 2" .
  • the first turbine upper part 1' and a first turbine housing lower part 1" are joined together at a longitudinal split plain 3 also the second turbine upper part 2' and a second turbine housing lower part 2".
  • the first turbine housing 1 and the second turbine housing 2 are joined together in longitudinal direction at a circumferential split plain 4.
  • Fig.2 shows the detail A of Fig.1 ..
  • flanges 5 are provided, which compress the split plains 3, 4 by means of bolts 6.
  • the longitudinal split and the circumferential split intersect at line, wherein this intersection line is line of so called cross-joint-line.
  • a hole 7 is drilled and closed by a pin 8.
  • the hole 7 is, preferably drilled in radial direction, and is formed and arranged in a manner, so that there is no common contact of all turbine housing parts 1', 1", 2', 2" together when these parts assembled, so that connected turbine housing parts can mechanically only interact with adjacent part.
  • the hole 7 is pre-machined. That disconnects mutual interaction of diagonally connected turbine housing parts 1', 1", 2', 2" during assembly.
  • the final shape of the hole 7 shall be preferably drilled or manufactured in any other way, fine machined after all turbine housing parts 1', 1", 2', 2" are assembled. It shall be left enough material around the pin 8 to allow fine hole to be re-machined when the turbomachinery housing assembly is opened for revision, repairs etc..
  • the pin 8 has to be stiff just enough to stay in inside the hole 7 under the pressure and temperature load of the turbomachinery housing assembly. It has to be enough strain inside of pin 8, the wall material should creating high enough contact pressure to tight the pin 8 and stay there due to the friction force. At the same time the pin 8 has to be flexible enough to disconnect contact areas of turbine housing parts which are not adjacent. That means contact area 9 from contact area 11 and contact area 10 from contact area 12.
  • the pin 8 is, to fulfil these requirements, prefer designed as a hollow caped pin as shown in Fig.2 and 3a, 3b .
  • Fig. 3 shows a cross-section view B-B of cylindrical hollow caped pin 8 inside the hole 7.
  • the cylindrically shape is the easiest for and therefore the cheapest.
  • the hole 7 could be drilled by a commercial drill and the pin 8 is also easy to manufacture.
  • Drilled hole 7 is equipped by two different diameters 7', 7". Diameter of the hole 7' end connected with outer turbine space is greater than diameter 7" connected to inner space. This ensures that pin 8 cannot fall inside turbine casing.
  • On the turbine casing outer surface is made provision for securing the pin 8 inside the hole 7 in the form of planned area 13 around the hole of the pin 8. There are some threaded wholes 14 made into this area.
  • Fig. 4 shows securing the pin 8 using of a cover 15 by screws 16.
  • the hollow form of the pin independent of the outer shape of the pin, provides the necessary flexibility as well as the necessary stiffness.
  • the pin should be caped to prevent steam leakage or in-leakage. To hold the pin inside the hole, additional safety precautions could be provide.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19165437.5A 2019-03-27 2019-03-27 Turbomaschinengehäuseanordnung Withdrawn EP3715590A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19165437.5A EP3715590A1 (de) 2019-03-27 2019-03-27 Turbomaschinengehäuseanordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19165437.5A EP3715590A1 (de) 2019-03-27 2019-03-27 Turbomaschinengehäuseanordnung

Publications (1)

Publication Number Publication Date
EP3715590A1 true EP3715590A1 (de) 2020-09-30

Family

ID=66041128

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19165437.5A Withdrawn EP3715590A1 (de) 2019-03-27 2019-03-27 Turbomaschinengehäuseanordnung

Country Status (1)

Country Link
EP (1) EP3715590A1 (de)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09133026A (ja) * 1995-11-13 1997-05-20 Hitachi Ltd ガスタービン及びそのケーシング
EP1878880A1 (de) * 2006-07-11 2008-01-16 ALSTOM Technology Ltd Kreuzflanschdichtung für einen Druckbehälter, insbesondere für ein Turbomaschinengehäuse
EP2096272A1 (de) * 2008-02-27 2009-09-02 Siemens Aktiengesellschaft Geteiltes Turbomaschinengehäuse mit optimierten Teilfugenflanschen
WO2015116277A2 (en) * 2013-11-14 2015-08-06 United Technologies Corporation Flange relief for split casing
EP3103972A1 (de) * 2015-06-10 2016-12-14 United Technologies Corporation Innendurchmesser-muschelgehäuseflansch für ein gehäuse eines gasturbinenmotors
US20170198741A1 (en) * 2011-03-21 2017-07-13 Jpb Systeme Self-Locking Sealing Device

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09133026A (ja) * 1995-11-13 1997-05-20 Hitachi Ltd ガスタービン及びそのケーシング
EP1878880A1 (de) * 2006-07-11 2008-01-16 ALSTOM Technology Ltd Kreuzflanschdichtung für einen Druckbehälter, insbesondere für ein Turbomaschinengehäuse
EP2096272A1 (de) * 2008-02-27 2009-09-02 Siemens Aktiengesellschaft Geteiltes Turbomaschinengehäuse mit optimierten Teilfugenflanschen
US20170198741A1 (en) * 2011-03-21 2017-07-13 Jpb Systeme Self-Locking Sealing Device
WO2015116277A2 (en) * 2013-11-14 2015-08-06 United Technologies Corporation Flange relief for split casing
EP3103972A1 (de) * 2015-06-10 2016-12-14 United Technologies Corporation Innendurchmesser-muschelgehäuseflansch für ein gehäuse eines gasturbinenmotors

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