EP1106785A1 - Conduit pour fluide de fuite dans le rotor d'une turbomachine - Google Patents

Conduit pour fluide de fuite dans le rotor d'une turbomachine Download PDF

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Publication number
EP1106785A1
EP1106785A1 EP00120564A EP00120564A EP1106785A1 EP 1106785 A1 EP1106785 A1 EP 1106785A1 EP 00120564 A EP00120564 A EP 00120564A EP 00120564 A EP00120564 A EP 00120564A EP 1106785 A1 EP1106785 A1 EP 1106785A1
Authority
EP
European Patent Office
Prior art keywords
carrier ring
seal carrier
leakage
housing
turbo machine
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
EP00120564A
Other languages
German (de)
English (en)
Other versions
EP1106785B1 (fr
Inventor
Alexander Böck
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1106785A1 publication Critical patent/EP1106785A1/fr
Application granted granted Critical
Publication of EP1106785B1 publication Critical patent/EP1106785B1/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
    • F01D25/24—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D25/145—Thermally insulated casings
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer

Definitions

  • the invention relates to a turbomachine according to the preamble of the claim 1.
  • the casing and the casing are generally tried Housing cladding as good as possible against that in a main flow channel isolated working gas to isolate an acceptable gap behavior to maintain the moving gaps of the moving blades. It will continue to try To keep the housing temperature as low as possible in order to be inexpensive To be able to use material such as steel.
  • Efforts have already been made in technology to cool the housing and optimize the airflow. So describes the WO 92/17686 a turbine housing, which by the special design the housing cladding the air flow of the cooling air between the cladding and regulated outer circumference. It tries by narrowing the flow cross section over housing sections with a particularly thick Cross section to achieve increased cooling of these sections.
  • the mixed air flow which is also relatively hot due to the hot leakage air flow 24 flows out of this leakage air flow 24 and the throttle air 8 or penetrates the insulating elements 19 and consequently sets their insulating effect significantly lower than the housing section 10.
  • the housing section 10 can thereby be overheated at worst.
  • the leakage air flow 24 the resulting from the leak on the low pressure side, the insulating elements 19 of the seal carrier ring 7 from all sides with air higher Temperature flows around. Their insulating effect in the direction of the housing wall thus greatly reduced. As is known, this has a negative effect on the running column and thus on the turbine efficiency, since the increased by the way Heat transfer the entire area of the turbine housing thermally is deformed more quickly, i.e.
  • the present invention is therefore based on the object, the disadvantages to avoid the prior art and a simple and inexpensive Solution for removing those escaping from the main turbine flow channel to find hot working gases, the turbine efficiency improved and overheating of housing parts should be avoided.
  • a development of the present invention according to the features of Claim 2 provides a particularly advantageous design in front. This creates an at least partially double-walled seal carrier ring generated in the leakage air flow through the double-walled Section is channeled.
  • the baffle can advantageously according to the features of Claim 3 be attached to the seal carrier ring. But also other variants, such as individual tubes, longitudinally permeable metal honeycombs or metal bars are possible.
  • the seal carrier ring can for example made of a nickel-based alloy, such as Inconel 718 his.
  • a further advantageous embodiment of the present invention has the features of claim 4.
  • the openings are arranged according to the features of claim 5.
  • the openings lie at an end of the connecting gap facing the main flow channel of the turbomachine.
  • a particularly advantageous embodiment of the present invention is achieved with the features of claim 6.
  • the guide plate has a double function, since it also serves here as a holder for the seal carrier ring on a protruding circumferential retaining lug of the housing segment. This double function saves an additional mounting component.
  • a further advantageous embodiment of the present invention has the features of patent claim 7. In particular in a low-pressure turbine stage of a turbomachine, significant increases in efficiency can be achieved by designing the seal carrier ring accordingly.
  • FIG. 1 shows schematically a low-pressure turbine stage of an axial turbomachine in longitudinal section.
  • the main flow direction of the turbine runs in the drawing plane from left to right, i.e. from a stator 18 to a stator 13.
  • the cross section of the turbine widens conically in the direction of the stator 13.
  • the stator 18 is one in the axial direction Downstream rotor stage with rotor blades 14.
  • the stator feet 17, 29, each Have stator segments with several stators 18 and 13, and the seal carrier ring 7 are each connected to housing sections 27, 10 which form a gas-tight seal against the environment.
  • the housing sections 27, 10 are in turn on the outer circumference of a housing cladding 11 surrounded, in particular the guidance of cooling air serves.
  • the rotor blades 14 each have sealing tips at their blade tips 15, with a labyrinth seal attached to the seal carrier ring 7 12 cooperate to avoid flow losses.
  • On the Another stator 13 follows the rotor stage. Each of them consists of several stators 18, 13 stator segments formed are on stator feet 17, 29 on the turbine housing attached. Between its housing sections 10 and Rotor blades 14 is the rotating one on the already mentioned seal carrier ring 7 Labyrinth seal 12 arranged, in which the sealing tips 15th of the rotor blades 14 when the rotor blades expand due to temperature and centrifugal forces can work into it.
  • isolation space 21 is formed, in which first insulating elements 30 and second insulating elements 19 are arranged virtually behind it.
  • the housing sections 27 and 10 are via a housing screw 16 connected together. There is a circumferential one on the housing section 10 Hold nose 23 out, as shown in Figure 2 in detail.
  • This revolving Retaining lug 23 is from above and below through one end of the seal carrier ring 7 and one end of a baffle explained in more detail later 1 includes so that they as a holder of the seal carrier ring 7 its end facing the stator 18 is used. At its the stator 13 facing end is the seal carrier ring 7 in a groove-shaped in Recessing circumferential recess 28 of the stator 29 is added.
  • FIG. 1 shows an embodiment of a leakage current channel according to the invention 4 for channeling leakage flow, which is shown in detail in FIG is.
  • the leakage flow channel 4 is in the circumferential direction of the turbine by an annular wall of the seal carrier ring 7 and an annular Baffle 1 limited, these two components by so-called.
  • Spacer plates 2, which at regular intervals on the circumference are distributed, are spaced apart.
  • the leakage current channel 4 thus has a rectangular flow cross section in the present exemplary embodiment on.
  • connection gap 22 There is a connecting gap between the stator foot 17 and the seal carrier ring 7 22 formed.
  • Side of the connecting gap 22 is an annular cavity 5 between Stator foot 17 and housing section 27 formed. Furthermore, the seal carrier ring 7 in the amount of the connecting gap 22 holes 3 through which the connection gap 22 is connected to the leakage current channels 4.
  • the entire turbine housing is otherwise surrounded by a casing 11, via a screw connection 20 to the housing sections 10 connected is.
  • throttle air 8 comes from the upstream one High pressure turbine coming in as sealing air used there the cavity 5 and continues in the direction of the falling pressure the isolation room 21 introduced.
  • a leakage air flow 24 also arrives in the form of a fraction of the hot working gas from the main flow channel 6 through the connecting gap 22 in the direction of the falling Pressure, i.e. towards the cavity 5. This leakage air flow is now passed through the bore 3 into the leakage current channel 4. This will make the Leakage air flow 24 defined on the insulating elements 19 on the outside of the seal carrier ring 7 passed.
  • this hot air leakage mixture 25 is on the outside of the seal carrier ring 7 in the leakage current channel 4, where it cool can and at the outlet of the leakage duct 4 entrained by further throttle air and following the wall of the seal carrier ring 7 into one Cavity 9 can emerge.
  • the channel cross section of the leakage current channel 4 is designed so that whose flow resistance is much lower than that with insulation elements 19 is largely filled isolation space 21 around the ensure the desired flow pattern.
  • the arrangement of the holes 3 is chosen so that the throttle air 8, which is of course colder is as the working gas in the main flow channel 6, also through the Bores 3 flows into the leakage current channels 4. Only if the amount of Throttle air 8 is less than the amount of leakage in those already mentioned Cavity 9 of the seal carrier ring 7 on that facing the recess 28 Exits at the end, so additional leakage air working gas 24 is emitted the main flow channel 6 through the connecting gap 22 and the holes 3 drawn into the leakage current channels 4. The leakage air working gas or the leakage air flow 24 penetrates due to the arrangement of the holes 3 not in the cavity 5. This will make the turbine housing or the housing sections 10, 27 are additionally protected against overheating.
  • the leakage current channel 4 must not run over the entire length of the seal carrier ring 7. Rather, it is sufficient if the leakage current channel 4 is downstream of the first insulating element 30 or shortly after the start of the second insulating element 19 ends. This insulating element 19 then takes over the management of the leakage air mixture 25 essentially into the cavity 9. An unwanted one Flow around the insulating elements 30 and 19 and in particular the undesirable direct application of the housing section 10 with the Leakage air flow 24 can therefore no longer take place.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00120564A 1999-12-07 2000-09-20 Conduit pour fluide de fuite dans le rotor d'une turbomachine Expired - Lifetime EP1106785B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19958809A DE19958809A1 (de) 1999-12-07 1999-12-07 Leckstromkanal
DE19958809 1999-12-07

Publications (2)

Publication Number Publication Date
EP1106785A1 true EP1106785A1 (fr) 2001-06-13
EP1106785B1 EP1106785B1 (fr) 2004-01-14

Family

ID=7931629

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00120564A Expired - Lifetime EP1106785B1 (fr) 1999-12-07 2000-09-20 Conduit pour fluide de fuite dans le rotor d'une turbomachine

Country Status (2)

Country Link
EP (1) EP1106785B1 (fr)
DE (2) DE19958809A1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2867224A1 (fr) * 2004-03-04 2005-09-09 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
EP2696037A1 (fr) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Joint du canal d'écoulement d'une turbomachine
US20140044538A1 (en) * 2012-08-09 2014-02-13 MTU Aero Engines AG Clamping ring for a turbomachine
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
EP2725203A1 (fr) 2012-10-23 2014-04-30 MTU Aero Engines GmbH Conduite d'air froid dans une structure de boîtier d'une turbomachine
US20140186163A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Blade outer air seal having shiplap structure
US9506368B2 (en) 2012-10-30 2016-11-29 MTU Aero Engines AG Seal carrier attachment for a turbomachine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
US11933226B2 (en) 2022-05-13 2024-03-19 Rtx Corporation Heat shield and method of installing the same

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10122464C1 (de) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantelring

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US4719747A (en) * 1984-08-04 1988-01-19 MTU Motorern-und Turbinen-Union Munchen GmbH Apparatus for optimizing the blade and sealing slots of a compressor of a gas turbine
US5238365A (en) * 1991-07-09 1993-08-24 General Electric Company Assembly for thermal shielding of low pressure turbine
US5662457A (en) * 1993-09-13 1997-09-02 G&H Montage Gmbh Heat insulation assembly

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2257754B (en) * 1983-02-26 1993-09-29 Rolls Royce Improvements in or relating to axial flow gas turbines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US4719747A (en) * 1984-08-04 1988-01-19 MTU Motorern-und Turbinen-Union Munchen GmbH Apparatus for optimizing the blade and sealing slots of a compressor of a gas turbine
US5238365A (en) * 1991-07-09 1993-08-24 General Electric Company Assembly for thermal shielding of low pressure turbine
US5662457A (en) * 1993-09-13 1997-09-02 G&H Montage Gmbh Heat insulation assembly

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2867224A1 (fr) * 2004-03-04 2005-09-09 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
EP1577506A1 (fr) * 2004-03-04 2005-09-21 Snecma Dispositif de mainten axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
US7360989B2 (en) 2004-03-04 2008-04-22 Snecma Device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine
CN1664318B (zh) * 2004-03-04 2010-12-08 斯奈克玛公司 用于轴向保持涡轮机高压涡轮环形垫片段的装置
US9512734B2 (en) 2012-08-09 2016-12-06 MTU Aero Engines AG Sealing of the flow channel of a turbomachine
EP2696037A1 (fr) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Joint du canal d'écoulement d'une turbomachine
US9664065B2 (en) * 2012-08-09 2017-05-30 MTU Aero Engines AG Clamping ring for a turbomachine
US20140044538A1 (en) * 2012-08-09 2014-02-13 MTU Aero Engines AG Clamping ring for a turbomachine
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
US9605551B2 (en) 2012-10-12 2017-03-28 MTU Aero Engines AG Axial seal in a casing structure for a fluid flow machine
EP2725203A1 (fr) 2012-10-23 2014-04-30 MTU Aero Engines GmbH Conduite d'air froid dans une structure de boîtier d'une turbomachine
US9488069B2 (en) 2012-10-23 2016-11-08 MTU Aero Engines AG Cooling-air guidance in a housing structure of a turbomachine
US9506368B2 (en) 2012-10-30 2016-11-29 MTU Aero Engines AG Seal carrier attachment for a turbomachine
EP2938839A4 (fr) * 2012-12-31 2016-08-03 United Technologies Corp Joint d'étanchéité à l'air extérieur de pale ayant une structure à feuillure
US20140186163A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Blade outer air seal having shiplap structure
US9803491B2 (en) 2012-12-31 2017-10-31 United Technologies Corporation Blade outer air seal having shiplap structure
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
US11933226B2 (en) 2022-05-13 2024-03-19 Rtx Corporation Heat shield and method of installing the same

Also Published As

Publication number Publication date
EP1106785B1 (fr) 2004-01-14
DE50005016D1 (de) 2004-02-19
DE19958809A1 (de) 2001-06-13

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