EP1106785B1 - 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
EP1106785B1
EP1106785B1 EP00120564A EP00120564A EP1106785B1 EP 1106785 B1 EP1106785 B1 EP 1106785B1 EP 00120564 A EP00120564 A EP 00120564A EP 00120564 A EP00120564 A EP 00120564A EP 1106785 B1 EP1106785 B1 EP 1106785B1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
carrier ring
seal carrier
leakage
housing
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.)
Expired - Lifetime
Application number
EP00120564A
Other languages
German (de)
English (en)
Other versions
EP1106785A1 (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 preserve the blades of the blades. It will continue to try Keep 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.
  • leakage air flow 24 In the low-pressure turbine stage shown in a longitudinal section in FIG. 3 according to the known prior art, hot working gas is made the turbine main flow channel 6 through a connecting gap 22 in a space 5 is drawn in in the form of a so-called leakage air flow 24.
  • this Room 5 mixes this leakage air flow 24 with a specifically provided one or flow of throttle air 8 introduced into this space 5, which is essentially sealing air from this low pressure turbine stage upstream high-pressure turbine stage.
  • This Mixed air flow (referred to later as leakage air mixture 25) flows into an insulation space 21 via a so-called groove-nose connection 23 one between the seal carrier ring 7 and the Inner circumference of the turbine housing section 10 is provided, and in the insulating elements 19 are provided.
  • the mixed air flow which is also relatively hot due to the hot leak 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. At least however, by guiding the leakage air flow 24, the results from the leak on the low pressure side, the insulating elements 19 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 casing thermally is deformed faster, 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, with 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.
  • Another 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 a low-pressure turbine stage of a turbomachine in particular, significant increases in efficiency can be achieved by appropriately designing the seal carrier ring.
  • FIG. 1 shows schematically a low pressure turbine stage of an axial turbomachine in longitudinal section.
  • the main flow direction of the turbine runs here 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 Rotor stage with rotor blades 14 connected downstream.
  • the stator feet 17, 29, each Have stator segments with a plurality of stators 18 and 13, and the seal carrier ring 7 are each connected to housing sections 27, 10 which form a gas-tight seal from the environment.
  • the housing sections 27, 10 are in turn on their 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 A further stator 13 follows the rotor stage. 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 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.
  • On its stator 13 facing end is the seal carrier ring 7 in a groove-shaped in Recess 28 circumferential direction 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.
  • 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 output of the leakage flow channel 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)

Claims (7)

  1. Turbomachine ayant dans la zone d'un étage de rotor des isolations (19, 30) entre un anneau de support de joint (7) et un segment de carter (10),
    caractérisée par
    un canal de flux de fuite (4) pour canaliser le flux de fuite au niveau des isolations (19, 30).
  2. Turbomachine selon la revendication 1,
    caractérisée en ce que
    le canal de flux de fuite (4) est formé entre une tôle de guidage (1) et la périphérie extérieure de l'anneau de support de joint (7).
  3. Turbomachine selon la revendication 2,
    caractérisée par
    des tôles d'écartement (2) réparties à intervalles réguliers dans la direction périphérique entre la tôle de guidage (1) et la périphérie extérieure de l'anneau de support de joint (7).
  4. Turbomachine selon l'une des revendications précédentes,
    caractérisée par
    des orifices (3) répartis à la périphérie de l'anneau de support de joint (7), par lesquels du gaz chaud est fourni au canal de flux de fuite (4).
  5. Turbomachine selon la revendication 4,
    caractérisée en ce que
    les orifices (3) sont prévus dans un intervalle de liaison (22) entre une cavité (5) et un canal de flux principal (6).
  6. Turbomachine selon l'une des revendications précédentes,
    caractérisée en ce que
    la tôle de guidage (1) constitue en même temps la tôle de fixation de l'anneau de support de joint (7) au carter (10).
  7. Turbomachine selon l'une des revendications précédentes,
    caractérisée en ce que
    le canal de flux de fuite (7) est appliqué à l'étage de la turbine basse pression.
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
DE19958809 1999-12-07
DE19958809A DE19958809A1 (de) 1999-12-07 1999-12-07 Leckstromkanal

Publications (2)

Publication Number Publication Date
EP1106785A1 EP1106785A1 (fr) 2001-06-13
EP1106785B1 true 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 (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
EP2728122A1 (fr) 2012-10-30 2014-05-07 MTU Aero Engines GmbH Fixation de support d'étanchéité pour turbomachine
EP4276282A1 (fr) * 2022-05-13 2023-11-15 RTX Corporation Bouclier thermique et son procédé d'installation

Families Citing this family (7)

* 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
FR2867224B1 (fr) * 2004-03-04 2006-05-19 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
EP2696036A1 (fr) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Collier de serrage pour turbomachine
ES2620482T3 (es) 2012-08-09 2017-06-28 MTU Aero Engines AG Impermeabilización del canal de flujo de una turbomáquina
EP2725203B1 (fr) 2012-10-23 2019-04-03 MTU Aero Engines AG Conduite d'air froid dans une structure de boîtier d'une turbomachine
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

Family Cites Families (5)

* 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
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
DE3428892A1 (de) * 1984-08-04 1986-02-13 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Schaufel- und dichtspaltoptimierungseinrichtung fuer verdichter von gasturbinentriebwerken, insbesondere gasturbinenstrahltriebwerken
US5238365A (en) * 1991-07-09 1993-08-24 General Electric Company Assembly for thermal shielding of low pressure turbine
DE4331060C1 (de) * 1993-09-13 1994-06-30 Gruenzweig & Hartmann Montage Wärmedämmanordnung

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
EP2728122A1 (fr) 2012-10-30 2014-05-07 MTU Aero Engines GmbH Fixation de support d'étanchéité pour turbomachine
EP4276282A1 (fr) * 2022-05-13 2023-11-15 RTX Corporation Bouclier thermique et son procédé d'installation

Also Published As

Publication number Publication date
DE19958809A1 (de) 2001-06-13
DE50005016D1 (de) 2004-02-19
EP1106785A1 (fr) 2001-06-13

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