EP2543826A2 - Virole composite - Google Patents

Virole composite Download PDF

Info

Publication number
EP2543826A2
EP2543826A2 EP12174977A EP12174977A EP2543826A2 EP 2543826 A2 EP2543826 A2 EP 2543826A2 EP 12174977 A EP12174977 A EP 12174977A EP 12174977 A EP12174977 A EP 12174977A EP 2543826 A2 EP2543826 A2 EP 2543826A2
Authority
EP
European Patent Office
Prior art keywords
shroud
ring
engine
slots
arc length
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Withdrawn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
EP12174977A
Other languages
German (de)
English (en)
Other versions
EP2543826A3 (fr
Inventor
Paul F. Croteau
Kevin E. Green
Jun Shi
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2543826A2 publication Critical patent/EP2543826A2/fr
Publication of EP2543826A3 publication Critical patent/EP2543826A3/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the present disclosure is directed to a geometry to minimize feature related thermal stresses in a monolithic ceramic or Ceramic Matrix Composite (CMC) shroud used in a gas turbine engine.
  • CMC Ceramic Matrix Composite
  • a ceramic or CMC shroud in the hot section of a gas turbine engine as a replacement of a similar metallic component is beneficial.
  • a metal shroud requires substantial cooling in order to withstand the high temperature in the turbine section.
  • a metal shroud is composed of multiple arc sections held by a complex assembly of support hardware to provide close positional tolerance and circularity to provide gap control with the rotor blade tips.
  • a one piece ceramic shroud by virtue of its inherent thermal material properties and high temperature capability, provides the ability to reduce the running blade tip clearance and reduced cooling air, providing improvements in efficiency and increased power.
  • a simple ring structure provides the most stable structure with the least distortion and lowest thermal stress.
  • Various techniques exist for shroud support which require designing and fabricating the shroud ring structure with features onto which to support and locate the shroud within the metal assembly.
  • Features may range from tabs or protrusions on the outer diameter surface or on one or both end faces, to slots or grooves on the outer diameter surface of the shroud.
  • a shroud comprising a ring with a plurality of protrusions and a plurality of slots and each of said protrusions having an arc length and parallel sides.
  • an engine broadly comprising a rotor and ceramic shroud surrounding said rotor and said shroud comprising a ring with a plurality of protrusions and a plurality of slots and each of said protrusions having an arc length and parallel sides.
  • a cross section of an engine 10 The engine includes a compressor 12 through which a fluid flows and is compressed, a combustor 14 in which the compressed fluid is mixed with a fuel and combusted, and a turbine section 24 in which the heated fluid is expanded to drive the turbine for creating power to drive the compressor 12 and other systems.
  • the turbine section 24 includes a turbine vane 16, a turbine shroud 18, a turbine rotor 20, and a turbine support case 22.
  • the ideal structure would be a simple ring structure. This is because such a structure provides the most stable structure with the least distortion and lowest thermal stress.
  • the ring structure of shroud 18 as shown in Fig. 2 may have a plurality of outer diameter protrusions 30 creating slots 34 with parallel sides 32.
  • the use of parallel sides 32 across slot 34 is useful and relevant when the arc length of slot A1 is much less than arc length of A2.
  • a simple ring provides the hoop strength and the stable structure needed to withstand the thermal gradient that the shroud 18 will be exposed to.
  • the loading experienced in the ring structure from a through thickness temperature gradient is a bending load, with the hotter inner diameter surface in compression and the cooler outer diameter surface in tension. If the ring were unwrapped into a simply supported flat bar, the temperature gradient would cause a differential of thermal expansion from one side to the other and cause the bar to bend. To eliminate the deformation from the flat bar, a pure moment, equal and opposite, would need to be applied at each end of the bar.
  • a featureless ring though, is not practical and some means are needed to provide support and location of the ring structure to the assembly.
  • Various features pertaining to assembly have been proposed and may be valid for reasons specific to the design requirements. But once a feature is introduced into the structure of the ring and eliminates the constant cross section of the ring, the bending load in the ring becomes evident through higher strains and ring distortion. Depending on the feature, the distortion and localized high strain can cause increased stress and stress concentrations. These stress concentrations are most often associated with fillets at the attachment feature and are inherently tensile surface stresses or 1st principal stresses.
  • the shroud 18 is provided with a plurality of slots 34 bordered by the sides 32 of adjacent protrusions 30.
  • Each slot 34 has an inner surface 36 which may be either a flat surface of a curved surface with a radius R1. Further, each slot 34 has a slot arc length A1. As noted before, each protrusion 30 has an arc length A2.
  • the slots 34 may be equally spaced around the periphery of the shroud 18. There may be from 3 to 18 slots 34. Each slot 34 may have an arc length in the range of 20 to 60 degrees.
  • the sides 32 of the slots 34 are parallel. With a multitude of identical slots positioned around the circumference of the ring 38 forming the shroud 18, concentric and circumferential position of the ring 38 can be maintained with a mating ring 40 with mating features 42 that contact the parallel sides 32 of each slot as shown in Fig. 5 .
  • the parallel sides 32 of each slot 34 allows thermal expansion of the ring 38 relative to its support ring 40 with introducing additional stress due to thermal mismatch between mating parts.
  • slot arc lengths much less than protrusion arc lengths, or A1 ⁇ A2, than a majority of the ring 38 is dominated by the maximum ring thickness T2.
  • This provides a stiffer cross section to withstand the bending load from the through thickness thermal gradient. This may cause a significant stress riser in the fillet region 33 of the slots 34 where the stress increases with decreasing slot arc length.
  • Fig. 5 shows the relationship of stress concentrations for a shroud ring 38 with varying arc lengths of protrusions 30 and slots 34, where the stress is normalized relative to the maximum stress condition for a 5 slot ring.
  • a thermal finite element model was solved for a given temperature gradient through the thickness of the ring. The thermal solution was then passed to a structural finite element model to solve for the thermally induced stresses.
  • Curve 1 is for a ring with five slots and protrusions. It indicates that the stress concentration in the fillet region decreases significantly as the slot arc length increases, to about 1/3 of the maximum stress of that of the narrowest slot. Note that there appears to be an optimal protrusion arc length of approximately 20 degrees, or a slot arc length of 52 degrees, as illustrated by Curve 1 for the five slot/protrusion ring, where the stress concentration is at 27% of the maximum case.
  • Curve 2 in Fig. 5 is for a similar shroud ring with 12 slots and protrusions with similarly changing arc lengths.
  • the magnitude of the stress concentration is essentially equal for when arc lengths of the slots are at the maximum, or where the arc lengths of the protrusions are equal.
  • the maximum stress for when the slot is at its minimum is lower for the 12 slot ring as compared to the 5 slot ring, which is expected as 12 slots allow more deflection of the ring from the internal bending load induced from the through thickness temperature gradient. It is interesting to note that the same optimal protrusion arc length for the 5 slot case is not apparent for the 12 slot/protrusion case shown in Curve 2.
  • the maximum hoop stress of a plain ring thickness T1 is approximately 15% less than the lowest maximum stress condition, as shown by the dotted line 3 in Fig. 5 .
  • a featureless shroud ring is not a useful solution for assembly into the hot section of a gas turbine engine. Therefore, the geometry that provides the least thermally induced stress is a ring with a multitude of protrusions with an arc length as small as practical to provide adequate mounting support. From Fig. 5 , it is apparent that more slots for a given slot length will reduce the maximum stress. Also, Fig. 5 shows that as the slot length increases, the maximum stress decreases, indicating that protrusions are more desirable than slots, from a stress point of view.
  • a shroud 18 having 5 to 12 slots determining the number of useful slots to use in a particular design application depends on issues including manufacturing cost. It follows that the more features the ring will have will in turn increase the cost of the shroud ring. Close tolerance control in ceramic components requires much of the machining of the contact surfaces and other critical features need to be done in the ceramic's hardened state. Therefore, to decrease manufacturing costs, as much machining in the green state should be performed prior to densification if the ceramic, leaving only a minimal amount of machining to obtain the required tolerance.
  • the shroud ring 18 may be formed from any suitable ceramic material known in the art.
  • the shroud ring 18 may be a monolithic ceramic material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12174977.4A 2011-07-05 2012-07-04 Virole composite Withdrawn EP2543826A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/176,112 US20130011248A1 (en) 2011-07-05 2011-07-05 Reduction in thermal stresses in monolithic ceramic or ceramic matrix composite shroud

Publications (2)

Publication Number Publication Date
EP2543826A2 true EP2543826A2 (fr) 2013-01-09
EP2543826A3 EP2543826A3 (fr) 2013-11-13

Family

ID=46458304

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12174977.4A Withdrawn EP2543826A3 (fr) 2011-07-05 2012-07-04 Virole composite

Country Status (2)

Country Link
US (1) US20130011248A1 (fr)
EP (1) EP2543826A3 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014120334A1 (fr) * 2013-01-29 2014-08-07 Sippel Aaron D Enveloppe de turbine
WO2015047478A2 (fr) 2013-07-23 2015-04-02 United Technologies Corporation Commande de position radiale de structure de support de carter à raccord cannelé
EP2942339A1 (fr) * 2014-05-08 2015-11-11 United Technologies Corporation Méthode de fabrication d'une fixation intégrale en matériau composite à matrice céramique, comprenant une étape de rigidification sans polymère
EP2942340A1 (fr) * 2014-05-08 2015-11-11 United Technologies Corporation Méthode de fabrication d'une fixation intégrale en matériau composite à matrice céramique, comprenant une étape de rigidification avec polymère
EP3045685A1 (fr) * 2014-12-15 2016-07-20 General Electric Company Fixation mécanique et agencement associé de fixation d'aube de redresseur
US10982564B2 (en) 2014-12-15 2021-04-20 General Electric Company Apparatus and system for ceramic matrix composite attachment
US12024474B2 (en) 2022-06-27 2024-07-02 Rtx Corporation Integral ceramic matrix composite fastener with polymer rigidization

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US10094233B2 (en) 2013-03-13 2018-10-09 Rolls-Royce Corporation Turbine shroud
US10378387B2 (en) 2013-05-17 2019-08-13 General Electric Company CMC shroud support system of a gas turbine
EP3080403B1 (fr) 2013-12-12 2019-05-01 General Electric Company Système de support de carénage cmc
EP3155231B1 (fr) 2014-06-12 2019-07-03 General Electric Company Ensemble dispositif de suspension de carénage
CA2951425C (fr) 2014-06-12 2019-12-24 General Electric Company Ensemble de suspension de carenage
CN106460543B (zh) 2014-06-12 2018-12-21 通用电气公司 多件式护罩悬挂器组件
US10190434B2 (en) 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
EP3034803A1 (fr) 2014-12-16 2016-06-22 Rolls-Royce Corporation Système de suspension d'un composant de moteur à turbine
CA2915246A1 (fr) 2014-12-23 2016-06-23 Rolls-Royce Corporation Enveloppe de turbine
CA2915370A1 (fr) 2014-12-23 2016-06-23 Rolls-Royce Corporation Chemin de pale circulaire comportant des elements clavetes axialement
EP3045674B1 (fr) 2015-01-15 2018-11-21 Rolls-Royce Corporation Enveloppe de turbine avec inserts tubulaires de localisation de patins
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
CA2925588A1 (fr) 2015-04-29 2016-10-29 Rolls-Royce Corporation Sillage de pale brase destine a une turbine a gaz
CA2924855A1 (fr) 2015-04-29 2016-10-29 Rolls-Royce Corporation Sillage de pale a distorsion trapezoidale
US10550709B2 (en) 2015-04-30 2020-02-04 Rolls-Royce North American Technologies Inc. Full hoop blade track with flanged segments
EP3109043B1 (fr) 2015-06-22 2018-01-31 Rolls-Royce Corporation Procédé d'assemblage intégral de composites à matrice céramique infiltrés
US10240476B2 (en) 2016-01-19 2019-03-26 Rolls-Royce North American Technologies Inc. Full hoop blade track with interstage cooling air
US10415415B2 (en) 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US10287906B2 (en) 2016-05-24 2019-05-14 Rolls-Royce North American Technologies Inc. Turbine shroud with full hoop ceramic matrix composite blade track and seal system
FR3076578B1 (fr) * 2018-01-09 2020-01-31 Safran Aircraft Engines Ensemble d'anneau de turbine
US10822964B2 (en) * 2018-11-13 2020-11-03 Raytheon Technologies Corporation Blade outer air seal with non-linear response
US10934941B2 (en) 2018-11-19 2021-03-02 Raytheon Technologies Corporation Air seal interface with AFT engagement features and active clearance control for a gas turbine engine
US10920618B2 (en) 2018-11-19 2021-02-16 Raytheon Technologies Corporation Air seal interface with forward engagement features and active clearance control for a gas turbine engine
US11015485B2 (en) 2019-04-17 2021-05-25 Rolls-Royce Corporation Seal ring for turbine shroud in gas turbine engine with arch-style support
US11939888B2 (en) * 2022-06-17 2024-03-26 Rtx Corporation Airfoil anti-rotation ring and assembly

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2580033A1 (en) * 1985-04-03 1986-10-10 Snecma Elastically suspended turbine ring for a turbine machine
JPH09264104A (ja) * 1996-03-27 1997-10-07 Ishikawajima Harima Heavy Ind Co Ltd セラミック製シュラウドリング
US8079807B2 (en) * 2010-01-29 2011-12-20 General Electric Company Mounting apparatus for low-ductility turbine shroud
US8784052B2 (en) * 2010-05-10 2014-07-22 Hamilton Sundstrand Corporation Ceramic gas turbine shroud
US8684689B2 (en) * 2011-01-14 2014-04-01 Hamilton Sundstrand Corporation Turbomachine shroud
US8511975B2 (en) * 2011-07-05 2013-08-20 United Technologies Corporation Gas turbine shroud arrangement

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014120334A1 (fr) * 2013-01-29 2014-08-07 Sippel Aaron D Enveloppe de turbine
EP3025042A4 (fr) * 2013-07-23 2016-08-17 United Technologies Corp Commande de position radiale de structure de support de carter à raccord cannelé
WO2015047478A2 (fr) 2013-07-23 2015-04-02 United Technologies Corporation Commande de position radiale de structure de support de carter à raccord cannelé
US10371011B2 (en) 2014-05-08 2019-08-06 United Technologies Corporation Integral ceramic matrix composite fastener with polymer rigidization
EP2942340A1 (fr) * 2014-05-08 2015-11-11 United Technologies Corporation Méthode de fabrication d'une fixation intégrale en matériau composite à matrice céramique, comprenant une étape de rigidification avec polymère
EP2942339A1 (fr) * 2014-05-08 2015-11-11 United Technologies Corporation Méthode de fabrication d'une fixation intégrale en matériau composite à matrice céramique, comprenant une étape de rigidification sans polymère
US10538013B2 (en) 2014-05-08 2020-01-21 United Technologies Corporation Integral ceramic matrix composite fastener with non-polymer rigidization
US11370714B2 (en) 2014-05-08 2022-06-28 Raytheon Technologies Corporation Integral ceramic matrix composite fastener with polymer rigidization
US11384020B2 (en) 2014-05-08 2022-07-12 Raytheon Technologies Corporation Integral ceramic matrix composite fastener with non-polymer rigidization
US11878943B2 (en) 2014-05-08 2024-01-23 Rtx Corporation Integral ceramic matrix composite fastener with non-polymer rigidization
EP3045685A1 (fr) * 2014-12-15 2016-07-20 General Electric Company Fixation mécanique et agencement associé de fixation d'aube de redresseur
US10982564B2 (en) 2014-12-15 2021-04-20 General Electric Company Apparatus and system for ceramic matrix composite attachment
US12024474B2 (en) 2022-06-27 2024-07-02 Rtx Corporation Integral ceramic matrix composite fastener with polymer rigidization

Also Published As

Publication number Publication date
EP2543826A3 (fr) 2013-11-13
US20130011248A1 (en) 2013-01-10

Similar Documents

Publication Publication Date Title
EP2543826A2 (fr) Virole composite
US11118477B2 (en) Turbine ring assembly
US8511975B2 (en) Gas turbine shroud arrangement
US7726936B2 (en) Turbine engine ring seal
CN107735549B (zh) 由法兰支撑的涡轮机环组件
US8651497B2 (en) Winged W-seal
US7950234B2 (en) Ceramic matrix composite turbine engine components with unitary stiffening frame
US7052235B2 (en) Turbine engine shroud segment, hanger and assembly
US7942004B2 (en) Tile and exo-skeleton tile structure
EP2500519B1 (fr) Aube rotorique de turbine
US10801729B2 (en) Thermally coupled CMC combustor liner
US8210799B1 (en) Bi-metallic strip seal for a turbine shroud
US10370986B2 (en) Nozzle and nozzle assembly for gas turbine engine
US10858958B2 (en) Turbine ring assembly held by jaw coupling
WO2010110325A1 (fr) Ensemble aube de stator de turbine cmc
RU2677021C1 (ru) Турбина
US10227880B2 (en) Turbine blade attachment mechanism
CN113195873A (zh) 具有分度法兰的涡轮环组件
CN108026785B (zh) 涡轮发动机的涡轮机、涡轮喷气发动机和飞机
GB2510218B (en) High-pressure turbine blades made of ceramic matrix composites
GB2565007A (en) Turbine ring assembly with cold setting
JP5595241B2 (ja) ガスタービン、分割セグメント、分割セグメントの形成方法
JP4020905B2 (ja) タービンノズルの両持型支持構造

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

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

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 25/24 20060101ALI20131004BHEP

Ipc: F01D 11/08 20060101ALI20131004BHEP

Ipc: F01D 9/04 20060101AFI20131004BHEP

17P Request for examination filed

Effective date: 20140513

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

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20170830

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: RAYTHEON TECHNOLOGIES CORPORATION

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20210202