EP4151836A2 - Élément de protection thermique pour chambre de palier d'une turbine à gaz - Google Patents

Élément de protection thermique pour chambre de palier d'une turbine à gaz Download PDF

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Publication number
EP4151836A2
EP4151836A2 EP22195459.7A EP22195459A EP4151836A2 EP 4151836 A2 EP4151836 A2 EP 4151836A2 EP 22195459 A EP22195459 A EP 22195459A EP 4151836 A2 EP4151836 A2 EP 4151836A2
Authority
EP
European Patent Office
Prior art keywords
heat protection
protection element
gas turbine
bearing chamber
axially
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.)
Pending
Application number
EP22195459.7A
Other languages
German (de)
English (en)
Other versions
EP4151836A3 (fr
Inventor
Florian Neuberger
Kaspar Wolf
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP4151836A2 publication Critical patent/EP4151836A2/fr
Publication of EP4151836A3 publication Critical patent/EP4151836A3/fr
Pending 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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2260/231—Preventing heat transfer
    • 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
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to a heat protection element for a gas turbine, in particular an aircraft gas turbine, which is set up to at least partially surround a bearing chamber of the gas turbine. Furthermore, the invention relates to a heat protection unit and a gas turbine with a heat protection element.
  • Bearing chambers in axially rear parts or areas of a gas turbine, in particular aircraft gas turbine, must be insulated from hot cavities in the gas turbine in order not to exceed a permissible temperature of circulating coolants, such as oil or the like.
  • a permissible temperature of circulating coolants such as oil or the like.
  • a bearing chamber is surrounded in the circumferential direction by a radially outer heat shield and a radially inner heat shield.
  • the radially inner heat shield is designed in two parts with a front and a rear heat protection shield, with both the front heat protection shield and the rear heat protection shield being materially connected to the bearing chamber, in particular welded or soldered. Due to the material connection, the inner heat protection shield cannot be removed from the storage chamber. This gives rise to the problem that the storage chamber cannot be inspected, or can only be inspected with difficulty. Furthermore, it has been shown that fretting can occur in particular at the connection points of the rear heat shield with the highly stressed bearing chamber.
  • the object on which the invention is based is seen as specifying a heat shield element for a gas turbine in which the above disadvantages can be avoided.
  • Such a configuration of the heat protection element can prevent fretting-causing contact between the heat protection element and the bearing chamber in the axially rear region. A distance of a few millimeters is formed between the end section and the storage chamber. Such a heat protection element thus enables good thermal shielding of the bearing chamber in its axially rear region, despite the contactless arrangement.
  • the heat protection element can be designed in one piece.
  • a one-piece or one-piece heat protection element arranged radially on the inside is proposed so that there is no longer any multiple parts and in particular a material-locking connection of an axially rear heat protection element can be dispensed with.
  • the heat protection element can be designed in such a way that it forms a heat protection unit together with the protection element of the seal carrier Flange portion of the storage chamber is fastened or fastened.
  • the heat protection unit can be connected to the flange section of the bearing chamber by means of screw connections running in the axial direction.
  • the heat protection element or the heat protection unit can be pushed onto the bearing chamber from the axial front or be removable from it.
  • the heat protection element surrounding the bearing chamber or the heat protection unit can be separated from the bearing chamber so that it can be inspected.
  • this also enables a simplified replacement of a heat protection element or a heat protection unit.
  • At least three tab-like connecting sections distributed in the circumferential direction can be formed in the axially front area.
  • a single circumferential connection section can be formed in the axially front area of the heat protection element, in particular in the form of a circumferential welded or soldered seam.
  • a connection is made by means of a press joint between the heat protection element and the protection element of the seal carrier.
  • the end section can be bent over axially to the front, in particular bent over in the manner of a rim.
  • Sufficient stability or rigidity of the end section can be achieved by such a reshaping of the end section, so that its non-contact arrangement in relation to the bearing chamber can be reliably ensured, in particular also during operation of the gas turbine and under corresponding thermal or mechanical loading.
  • At least three beads which are distributed in the circumferential direction and are shaped radially inward can be formed in the axially central region, which beads serve as respective support sections. It is of course also conceivable that more than three beads are provided. Furthermore, it is also conceivable that a continuous bead in the circumferential direction is formed.
  • a single circumferential support section can be provided in the axially central region, which can be or is in contact with a ring seal arrangement supported on the bearing chamber, in particular a sealing cord.
  • a ring seal arrangement can be accommodated, for example, in a groove-like recess provided on the outer circumference of the bearing chamber.
  • the support section on the heat protection element can also be designed without a special shape, in particular axially straight.
  • a heat protection unit for a bearing chamber of a gas turbine in particular an aircraft gas turbine, consisting of a heat protection element as described above and a further protection element of a seal carrier which is materially connected to the heat protection element in an axially front area of the heat protection unit.
  • a further protection element of a seal carrier which is materially connected to the heat protection element in an axially front area of the heat protection unit.
  • Optional configurations of the heat protection element described above can also be implemented or used for the heat protection unit.
  • the further protective element of the seal carrier can in particular be an essentially ring-shaped sleeve which surrounds and thermally shields a seal carrier for a carbon seal.
  • the carbon seal serves in particular to provide a seal with respect to a shaft of the gas turbine.
  • a gas turbine in particular an aircraft gas turbine, is proposed with at least one bearing chamber around which a heat protection element described above or a heat protection unit described above is arranged.
  • the heat protection element can be provided in the area of a turbine center frame or as part of a turbine center frame.
  • FIG. 1 shows a schematic and simplified view of an aircraft gas turbine 10, which is illustrated purely by way of example as a turbofan engine.
  • the gas turbine 10 includes a fan 12 surrounded by a jacket 14 that is indicated.
  • the fan 12 is followed by a compressor 16, which is accommodated in an indicated inner housing 18 and can be of single-stage or multi-stage design.
  • the compressor 16 is followed by the combustion chamber 20 .
  • Hot exhaust gas flowing out of the combustion chamber then flows through the adjoining turbine 22, which can be of single-stage or multi-stage design.
  • the turbine 22 includes a high-pressure turbine 24 and a low-pressure turbine 26.
  • a hollow shaft 28 connects the high-pressure turbine 24 to the compressor 16, in particular a high-pressure compressor 29, so that they are driven or rotated together.
  • a further inner shaft 30 in the radial direction RR of the turbine connects the low-pressure turbine 26 to the fan 12 and to a low-pressure compressor 32, so that they are driven or rotated together.
  • a thrust nozzle 33 which is only indicated here, is connected to the turbine 22 .
  • a turbine center frame 34 is arranged between the high-pressure turbine 24 and the low-pressure turbine 26, which is arranged around the shafts 28, 30.
  • hot exhaust gases from the high-pressure turbine 24 flow through the turbine center frame 34 .
  • the hot exhaust gas then reaches an annular space 38 of the low-pressure turbine 26.
  • Rotor blade rings 27 of the compressors 28, 32 and the turbines 24, 26 are shown by way of example.
  • guide vane rings 31 that are usually present are shown as an example only for compressor 32 .
  • FIG. 2 shows a heat protection element 50, which can be used in a gas turbine 10, in a simplified, schematic perspective representation.
  • an axis of rotation DA is indicated, which is aligned with the axes of the shafts 28, 30 ( 1 ) of the gas turbine coincide.
  • the heat protection element 50 is arranged in the area of a storage chamber in which at least one shaft 28, 30 of the gas turbine is mounted. Referring to 1 the heat protection element 50 can be arranged in particular in the region of the turbine center frame 34, in particular radially on the inside of the in 1 shown outer region 36 in which hot gas flows.
  • the heat protection element 50 has at least one connection section 52 in an axially front area VB.
  • the connection section(s) 52 are materially connected to a protective element 54 .
  • the protective element 54 surrounds or covers a seal carrier, not shown here.
  • the heat protective element 50 has a main body 56 which extends axially to the rear and has different radii over the axial length. In particular, the radius of the heat protection element 50 increases discretely or continuously in sections from the axial front to the axial rear.
  • a support section 58 is provided in an axially central area MB, which is set up to support the heat protection element 50 radially on a bearing chamber 60 shown in simplified form in the sectional illustrations.
  • the support of the heat protection element 50 can be done via a support element 62 in the 3 and 4 is shown only schematically and representative of different types of support.
  • the heat protection element 50 has an end section 64 which forms a free end 66 of the heat protection element 50 .
  • the end section 64 is shaped or bent over in such a way that the end section 64 surrounds the bearing chamber 60 in a contactless manner. In other words, a distance AB or intermediate space is formed between the end section 64 and the bearing chamber 60 .
  • Heat protection element 50 shown can be formed in one piece.
  • the connection sections 52, support section 58 and end section 64 described above are therefore produced from one workpiece or material.
  • the heat protection element 50 forms a heat protection unit 70 together with the protection element 54 of the seal carrier.
  • the heat protection unit 70 can be attached to an axially front flange section 72 which is 3 is only indicated, the storage chamber 60 can be fastened or fastened.
  • the heat protection unit 70 can, for example, be pushed onto the bearing chamber 60 from the axial front or removed from it.
  • At least three strap-like connecting sections 52 can be formed, distributed in the circumferential direction.
  • Such a configuration is exemplified by the 2 visible, with only two of several connecting sections 52 are shown.
  • the heat protection element 50 can have a single circumferential connection section 52 in the axially front region VB, in particular in the form of a circumferential welded or soldered seam.
  • the end section 64 of the heat protection element 50 is bent forward axially.
  • the end portion 64 can also be described as being bent over like a brim.
  • Such a reshaping of the end section 64 can achieve sufficient stability or rigidity of the end section 64 so that its non-contact arrangement (with distance BA or intermediate space) in relation to the bearing chamber 60 can be reliably ensured, in particular also during operation of the gas turbine 10 and under corresponding thermal or mechanical stress.
  • the above-mentioned, schematically and representatively illustrated support element 62 can, according to embodiments, be designed in such a way that in the axial central region MB at least three beads are formed on heat protection element 50, distributed in the circumferential direction and shaped radially inwards, which act as respective support sections 58 or support element 62 serve.
  • a single circumferential support section 58 can be provided in the axially central area MB, which can be or is in contact with a ring seal arrangement, in particular a sealing cord, supported on the bearing chamber 60 .
  • the support element 62 shown can also be understood as such a ring seal arrangement or represent such.
  • the heat protection unit 70 can, for example, be screwed to the storage chamber 60, which is achieved by the in 2 visible holes 74 in the protective element 54 is illustrated.
  • the axial areas VB, MB, HB can be established or defined, for example, based on a percentage of the axial length of the heat protection element 50 .
  • the front and rear areas VB, HB are each illustrated with approximately 20% of the axial extension of the heat protection element 50, with the central area MB being at approximately 60%.
  • This percentage distribution is purely exemplary; in particular, the front and rear areas VB can also be defined shorter or longer, for example in a range of approximately 5% to 30% of the axial extension of the heat protection element 50.
  • This results in the middle area MB can be about 40% to 90% of the axial extension.
  • a configuration of the heat protection element 50 presented above makes it possible to avoid contact between the heat protection element 50 and the bearing chamber 60 that causes fretting in the axially rear area HB.
  • the distance AB or intermediate space is formed between the end section 64 and the bearing chamber 60 .
  • This distance AB can be a few millimeters.
  • the heat protection element 50 presented here enables good thermal shielding of the bearing chamber 60.
  • heat protection element 50 Due to the one-piece design of the heat protection element 50, in contrast to previous heat protection elements, a one-piece or one-piece heat protection element 50 arranged radially on the inside is described , so that there is no longer a multi-part design and in particular a material-locking connection of an axially rear heat protection element can be dispensed with.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP22195459.7A 2021-09-21 2022-09-13 Élément de protection thermique pour chambre de palier d'une turbine à gaz Pending EP4151836A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021124357.2A DE102021124357A1 (de) 2021-09-21 2021-09-21 Hitzeschutzelement für eine Lagerkammer einer Gasturbine

Publications (2)

Publication Number Publication Date
EP4151836A2 true EP4151836A2 (fr) 2023-03-22
EP4151836A3 EP4151836A3 (fr) 2023-04-05

Family

ID=83319323

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22195459.7A Pending EP4151836A3 (fr) 2021-09-21 2022-09-13 Élément de protection thermique pour chambre de palier d'une turbine à gaz

Country Status (3)

Country Link
US (1) US11988106B2 (fr)
EP (1) EP4151836A3 (fr)
DE (1) DE102021124357A1 (fr)

Citations (3)

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Publication number Priority date Publication date Assignee Title
US9605551B2 (en) 2012-10-12 2017-03-28 MTU Aero Engines AG Axial seal in a casing structure for a fluid flow machine
US20190249569A1 (en) 2018-02-09 2019-08-15 MTU Aero Engines AG Bearing chamber housing for a turbomachine
US10415481B2 (en) 2013-03-11 2019-09-17 United Technologies Corporation Heat shield mount configuration

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DE10052122C1 (de) * 2000-10-19 2002-08-14 Zf Lemfoerder Metallwaren Ag Kugelgelenk
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US9605551B2 (en) 2012-10-12 2017-03-28 MTU Aero Engines AG Axial seal in a casing structure for a fluid flow machine
US10415481B2 (en) 2013-03-11 2019-09-17 United Technologies Corporation Heat shield mount configuration
US20190249569A1 (en) 2018-02-09 2019-08-15 MTU Aero Engines AG Bearing chamber housing for a turbomachine

Also Published As

Publication number Publication date
EP4151836A3 (fr) 2023-04-05
US20230184134A1 (en) 2023-06-15
US11988106B2 (en) 2024-05-21
DE102021124357A1 (de) 2023-03-23

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RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR