EP2570620A1 - Isolation thermique pour carter de turbine - Google Patents

Isolation thermique pour carter de turbine Download PDF

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Publication number
EP2570620A1
EP2570620A1 EP11181380A EP11181380A EP2570620A1 EP 2570620 A1 EP2570620 A1 EP 2570620A1 EP 11181380 A EP11181380 A EP 11181380A EP 11181380 A EP11181380 A EP 11181380A EP 2570620 A1 EP2570620 A1 EP 2570620A1
Authority
EP
European Patent Office
Prior art keywords
thermal insulation
turbine housing
thermal
insulating
insulating material
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Withdrawn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
EP11181380A
Other languages
German (de)
English (en)
Inventor
Pavel Rihak
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 EP11181380A priority Critical patent/EP2570620A1/fr
Publication of EP2570620A1 publication Critical patent/EP2570620A1/fr
Withdrawn legal-status Critical Current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
    • F01D25/08—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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the invention relates to a thermal insulation for a turbine housing and to a turbomachine having such a thermal insulation.
  • Turbine housings are equipped with a thermal insulation.
  • the thermal insulation is used to minimize the loss of heat via the turbine housing into the environment, since thermal losses result in reduced efficiency.
  • the thermal insulation is also used maintain the temperature of the components for as long as possible, in order thus to avoid lengthy heating up of the components of the steam turbine before it becomes operational in the morning. This means that the solar energy can be utilized more quickly, thereby resulting in more efficient operation of the turbine.
  • the turbine housing of a steam turbine is usually insulated using mineral wool in the form of mats. These insulating mats are fastened to the turbine housing by means of wires.
  • the rigid foams still have a high specific weight, however, and therefore a stable and secure fastening to the turbine housing must be ensured. Furthermore, the rigid foams only have a relatively modest thermal insulation.
  • the object of the invention is to provide a thermal insulation for a turbine housing, in particular for a steam turbine housing, which offers improved thermal insulation and lower specific weight at the same time.
  • the object of the present invention is to provide a turbomachine featuring an improved thermal insulation.
  • the object is achieved by the features in the independent claim 1.
  • the object is achieved by the features in the claim 12.
  • the inventive thermal insulation for a turbine housing is distinctive in that the thermal insulation consists of an insulating material or comprises an insulating material whose insulating properties are based essentially on nanostructures of the insulating material.
  • the structural properties can derive from the particle size, which lies in the nanometer range, from fibers whose diameter lies in the nanometer range, or from pore sizes in the nanometer range within the thermal insulation.
  • the thermal insulation can also be achieved by a combination of the individual structural measures. As a result of using thermal insulation featuring nanostructures, both significantly better insulating properties and a lower specific weight are produced in comparison with conventional insulating materials such as mineral fibers, for example.
  • the thermal insulation in its assembled state fits closely and essentially positively onto a corresponding contact surface of the turbine housing, either indirectly or directly.
  • the close fit of the thermal insulation against the turbine housing air gaps in which air circulation could occur are avoided. This produces a particularly effective thermal insulation.
  • the thermal insulation is connected to the turbine housing in such a way that it can be non-destructively disassembled.
  • the thermal insulation can easily be disassembled and then attached to the turbine housing again, particularly for the purpose of maintenance to the turbine.
  • the assembly time is shortened and the costs are considerably reduced in this way.
  • the thermal insulation consists of an aerogel or comprises an aerogel.
  • Aerogels are highly porous solids whose volume consists of up to 99.8% pores. Aerogels have a dendritic structure, meaning that there is significant branching of particle chains with numerous intermediate spaces in the form of open pores. This results in a stable sponge-like structure.
  • the aerogel has high strength and can be cut into a corresponding shape that matches the turbine housing, thereby ensuring all-over contact on the turbine housing.
  • the pore size of aerogels is in the nanometer range, and therefore large inner surfaces of up to 1000 sq.m/g can be achieved. Consequently, aerogels are particularly suitable for use as an insulating material.
  • the aerogel is a silica aerogel.
  • Silica aerogels have a melting point of approximately 1200° and are non-combustible and nontoxic. They are therefore particularly suitable for use as a thermal insulation for turbomachines in which high housing temperatures occur.
  • the individual particles of the silica aerogel have an average diameter of 1 to 10 nm.
  • the small particle size results in a fine branching of particle chains and hence a large number of intermediate spaces in the form of open pores in which air can be enclosed, wherein this contributes to particularly good thermal insulation.
  • the porosity of the silica aerogel is between 80 and 99.8%.
  • the high porosity contributes to a high inclusion of air and hence to better thermal insulation.
  • the thermal conductivity of the silica aerogel is between 0.017 and 0.021 W/mK. This ensures that the silica aerogel has high temperature stability, even under extreme conditions, and ensures good thermal insulation.
  • the thermal insulation consists of a nanofiber or comprises nanofibers.
  • a fiber whose average diameter is in the nanometer range is referred to as a nanofiber in this case.
  • the nanofibers have an average diameter between 50 and 500 nm.
  • the nanofiber is preferably a carbon fiber.
  • the nanofibers are woven into a textile thermal insulating mat.
  • the weaving of the nanofibers into a thermal insulating mat results in a very porous thermal insulating mat featuring the finest pores, in which air is enclosed, contributing to very good thermal insulation.
  • the insulating mats can be attached to the turbine housing easily. By virtue of the material that is used, the insulating mats have a very low specific weight and therefore sagging of the mat, as frequently occurs in the case of mineral fiber mats, can be avoided. Due to the increased porosity, they also exhibit significantly better thermal insulation than the mineral fiber insulating mats that were used previously.
  • the inventive turbomachine in particular a steam turbine, is distinctive in that the turbomachine features a thermal insulation as claimed in one of the preceding claims, i.e. it comprises a thermal insulation whose insulating properties are essentially based on nanostructures of the insulating material.
  • the nanostructures of the insulating material result in a particularly good thermal insulation and a very low specific weight at the same time.
  • improved thermal insulation improved efficiency of the turbomachine is achieved because thermal losses into the environment can be kept at a low level.
  • the low specific weight of the insulating material sagging of the insulating material is avoided, thereby preventing air gaps and therefore air circulation between insulating material and turbine.
  • turbomachines can be any type of turbomachine in which thermal insulation of the turbine housing relative to the environment is beneficial. Such thermal insulation is beneficial for steam turbines housings in particular, and here in particular for steam turbines which are used for solar thermal applications.
  • Figure 1 shows the exhaust-steam housing 2 of a steam turbine in a lateral sectional view.
  • the exhaust steam housing 2 has the form of a cone.
  • the exhaust steam housing 2 is designed to have a thermal insulation 1.
  • the thermal insulation 1 consists of an insulating material, whose insulating properties are based essentially on nanostructures of the insulating material.
  • suitable insulating materials include a silica aerogel or a textile thermal insulating mat woven from nanofibers, particularly carbon fibers.
  • the individual particles of the silica aerogel preferably have an average diameter of 1 to 10 nm.
  • the individual nanoparticles adhere to form finely branched particle chains, wherein the distance between the chains is preferably approximately 10 to 100 nm. This results in a multiplicity of fine pores in the nanometer range, whereby surfaces of up to 1000 sq.m/g insulating material can be achieved.
  • the porosity is between 80 and 99.8% in this case.
  • the high porosity results in a very low specific density of approximately 0.1 g/cm3.
  • the high porosity also results in a very low thermal conductivity of approximately 0.02 W/m*K in air at 300°K. This results in a very high level of thermal insulation.
  • the silica aerogel has the additional advantage of a very high melting point, this being approximately 1200°C.
  • the thermal insulation can be used not only for the relatively cool low-pressure region of steam turbines, but also for those steam turbine stages which are maintained at a considerably higher temperature or for other turbomachines such as gas turbines, for example.
  • the silica aerogel is a sponge-like but stable structure, which can be cut to shape or molded according to the requirements. As a result, it can be cut exactly to the contours of the turbine housing 2, thereby ensuring an all-over close fit of the thermal insulation 1 on the turbine housing 2 in the assembled state.
  • the positive fit of the thermal insulation 1 on the turbine housing 2 is realized by the corresponding contact surface 3 on the turbine housing 2 and on the thermal insulation 1. This prevents an air gap from developing between the turbine housing 2 and the thermal insulation 1. Air circulation could occur in the air gap and this would result in an increased heat emission into the environment.
  • the silica aerogel also has the advantage that it allows a high level of sound insulation. It is therefore possible to dispense with additional sound absorbing measures, thereby allowing cost savings. For example, a sound reduction of approximately 50% can be achieved at 100 Hz. Moreover, the silica aerogel is completely hydrophobic and weather-resistant, thereby eliminating the need for further coatings or protective measures such as those required for mineral wool, for example.
  • thermal insulation 1 Due to the extraordinarily low specific weight of the thermal insulation 1, sagging of the thermal insulation is completely prevented. Due to its development as a solid shaped part, the thermal insulation 1 can be assembled and disassembled easily and non-destructively, thereby offering particular advantages in the context of servicing. The thermal insulation 1 can easily be removed and then fastened to the turbine housing 2 again without great effort after servicing is complete. The service time and the service costs are reduced as a result of this.
  • the thermal insulation is advantageously designed in two parts. In this case, the fastening can be done by means of wires or Velcro connection or by other suitable means.
  • Figure 2 shows the front view of the turbine housing 2 with the thermal insulation 1.
  • the figure shows the thermal insulation 1 divided axially into two parts, consisting of an upper shell and a lower shell.
  • the upper shell 1' and the lower shell 1" can be connected together or fixed individually to the turbine housing 2 in each case.
  • the two-part design consisting of upper shell 1' and the lower shell 1" allows a simple and fully enclosing arrangement of the thermal insulation on the turbine housing 1.
  • a single-part solution would also be possible, but it would be necessary to ensure in this case that the thermal insulation could be pulled over the turbine housing 1 completely from the side.
  • thermal insulating mat which is made of nanofibers, in particular carbon fibers.
  • the thermal insulating mat is woven from nanofibers which have a diameter between 50 and 500 nm.
  • air is stored in the thermal insulating mat, thereby providing very good thermal insulation.
  • the thermal insulating mats can be fastened to the turbine housing 2 in a similar manner to the mineral fiber mats. Due to the significantly lower density of the thermal insulating mats, these being woven from nanofibers, sagging of the thermal insulating mats is effectively prevented.
  • the inventive thermal insulation significantly increases the thermal insulation, in comparison with conventional insulating materials, by means of an insulating material which exhibits insulating properties that are based essentially on the nanostructure of the insulating material.
  • the specific weight of the insulating material is clearly lower than in the case of previously used insulating materials.
  • the thermal insulation according to the invention allows increased efficiency to be achieved in the case of steam turbines in particular. In addition to the improved thermal insulation, it is also possible to achieve improved sound insulation and particularly good weather resistance.
  • the thermal insulation according to the invention can be disassembled non-destructively and can therefore be reused following servicing work on the turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Insulation (AREA)
EP11181380A 2011-09-15 2011-09-15 Isolation thermique pour carter de turbine Withdrawn EP2570620A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11181380A EP2570620A1 (fr) 2011-09-15 2011-09-15 Isolation thermique pour carter de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11181380A EP2570620A1 (fr) 2011-09-15 2011-09-15 Isolation thermique pour carter de turbine

Publications (1)

Publication Number Publication Date
EP2570620A1 true EP2570620A1 (fr) 2013-03-20

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP11181380A Withdrawn EP2570620A1 (fr) 2011-09-15 2011-09-15 Isolation thermique pour carter de turbine

Country Status (1)

Country Link
EP (1) EP2570620A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014213911A1 (de) * 2014-07-17 2016-01-21 MTU Aero Engines AG Aerogel-Auskleidungselement für Strömungsmaschinen
JP2020114999A (ja) * 2019-01-17 2020-07-30 三菱重工コンプレッサ株式会社 蒸気タービン、及び蒸気タービンの施工方法
US11098614B2 (en) * 2016-05-04 2021-08-24 Vitesco Technologies GmbH Turbine housing for a turbocharger of an internal combustion engine, and turbocharger
US20230193783A1 (en) * 2021-12-21 2023-06-22 Rolls-Royce Deutschland Ltd & Co Kg Fan case assembly for a gas turbine engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2267329A (en) * 1992-05-14 1993-12-01 Rolls Royce Plc Thermal insulation structure
US20040109758A1 (en) * 2002-12-06 2004-06-10 1419509 Ontario Inc. Insulation system for a turbine and method
EP1927728A2 (fr) * 2006-11-21 2008-06-04 General Electric Company Procédés pour réduire le stress dans le structures composites
DE102008002847A1 (de) * 2007-05-17 2008-11-20 General Electric Co. Dampfturbinenauslasshaube und Verfahren zur Herstellung derselben
DE102009013083A1 (de) 2009-03-13 2010-09-30 Siemens Aktiengesellschaft Turbinengehäuseisolierung
US20110052382A1 (en) * 2009-08-26 2011-03-03 Kin-Leung Cheung Composite casing for rotating blades
WO2011039050A2 (fr) * 2009-09-29 2011-04-07 Siemens Aktiengesellschaft Isolation thermique pour carter de turbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2267329A (en) * 1992-05-14 1993-12-01 Rolls Royce Plc Thermal insulation structure
US20040109758A1 (en) * 2002-12-06 2004-06-10 1419509 Ontario Inc. Insulation system for a turbine and method
EP1927728A2 (fr) * 2006-11-21 2008-06-04 General Electric Company Procédés pour réduire le stress dans le structures composites
DE102008002847A1 (de) * 2007-05-17 2008-11-20 General Electric Co. Dampfturbinenauslasshaube und Verfahren zur Herstellung derselben
DE102009013083A1 (de) 2009-03-13 2010-09-30 Siemens Aktiengesellschaft Turbinengehäuseisolierung
US20110052382A1 (en) * 2009-08-26 2011-03-03 Kin-Leung Cheung Composite casing for rotating blades
WO2011039050A2 (fr) * 2009-09-29 2011-04-07 Siemens Aktiengesellschaft Isolation thermique pour carter de turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
BUNDESMINISTERIUM FÜR BILDUNG UND FORSCHUNG: "Nano.DE Report 2009", 16 June 2009 (2009-06-16), XP055020334, Retrieved from the Internet <URL:http://www.bmbf.de/pub/nanode_report_2009.pdf> [retrieved on 20120227] *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014213911A1 (de) * 2014-07-17 2016-01-21 MTU Aero Engines AG Aerogel-Auskleidungselement für Strömungsmaschinen
US11098614B2 (en) * 2016-05-04 2021-08-24 Vitesco Technologies GmbH Turbine housing for a turbocharger of an internal combustion engine, and turbocharger
JP2020114999A (ja) * 2019-01-17 2020-07-30 三菱重工コンプレッサ株式会社 蒸気タービン、及び蒸気タービンの施工方法
JP7101625B2 (ja) 2019-01-17 2022-07-15 三菱重工コンプレッサ株式会社 蒸気タービン、及び蒸気タービンの施工方法
US20230193783A1 (en) * 2021-12-21 2023-06-22 Rolls-Royce Deutschland Ltd & Co Kg Fan case assembly for a gas turbine engine
US11753967B2 (en) * 2021-12-21 2023-09-12 Rolls-Royce Deutschland Ltd & Co Kg Fan case assembly for a gas turbine engine

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