EP2859189A1 - Dispositif d'assemblage pour un ensemble aube de stator - Google Patents

Dispositif d'assemblage pour un ensemble aube de stator

Info

Publication number
EP2859189A1
EP2859189A1 EP13796412.8A EP13796412A EP2859189A1 EP 2859189 A1 EP2859189 A1 EP 2859189A1 EP 13796412 A EP13796412 A EP 13796412A EP 2859189 A1 EP2859189 A1 EP 2859189A1
Authority
EP
European Patent Office
Prior art keywords
locating
fixture
vanes
pin
clamp
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
EP13796412.8A
Other languages
German (de)
English (en)
Other versions
EP2859189A4 (fr
EP2859189B1 (fr
Inventor
Michael E. Mcmahon
Steven J. Feigleson
Dennis R. Tremblay
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.)
Raytheon Technologies 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
Priority claimed from US13/483,501 external-priority patent/US8966755B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2859189A1 publication Critical patent/EP2859189A1/fr
Publication of EP2859189A4 publication Critical patent/EP2859189A4/fr
Application granted granted Critical
Publication of EP2859189B1 publication Critical patent/EP2859189B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures

Definitions

  • a gas turbine engine typically includes a fan section, and a core engine section including a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The highspeed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.
  • the compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines.
  • the high pressure turbine drives the high pressure compressor through an outer shaft to form a high spool
  • the low pressure turbine drives the low pressure compressor through an inner shaft to form a low spool
  • a direct drive gas turbine engine includes a fan section driven by the low spool such that the low pressure compressor, low pressure turbine and fan section rotate at a common speed in a common direction.
  • a speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
  • Some front architectures support the stator vanes relative to inner and outer fairings using rubber potting. Because there are no fixed features or fasteners used to secure vanes within the fairings, assembly can be difficult and time consuming.
  • a method of assembling a gas turbine engine front architecture includes securing inner and outer fairings within a fixture relative to one another, securing multiple vanes between the inner and outer fairing within the fixture, applying a curable material at an interface between each of the multiple vanes and the inner and outer fairings, curing the curable material while maintaining a relative position between the multiple vanes and the inner and outer fairings, and releasing the multiple vanes and the inner and outer fairings from the fixture.
  • a further embodiment of the foregoing method including positioning each of the multiple vanes within an opening of each of the inner and outer fairings.
  • a further embodiment of any of the foregoing methods including positioning each of the multiple vanes by defining a first plane with at least three (3) contact points on the fixture, a second plane with at least two (2) contact points on the fixture and a third plane with at least one (1) contact point defined on the fixture.
  • a further embodiment of any of the foregoing methods including defining the first plane with an outer locator pin on an outer locating ring of the fixture, an inner locator pin on an inner locating ring and a clamp disposed between the inner and outer locating rings.
  • a further embodiment of any of the foregoing methods including a single clamp for holding each of the vanes in position.
  • a further embodiment of any of the foregoing methods wherein the single clamp is disposed between the inner locating pin and the outer locating pin and includes a clamp portion supported on a clamp pin with the vane being clamped between the clamp portion and the clamp pin.
  • a further embodiment of any of the foregoing methods including defining the second plane with a surface of an outer locating ring and an inner locating ring.
  • a further embodiment of any of the foregoing methods including defining the third plane with a radial locating pin supported radially inward of the inner fairing.
  • a method of assembling a gas turbine engine front architecture includes [0016]
  • a fixture for assembling a stator vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing, an inner locating ring including a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing, a clamp section including a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings, and an inner locating section supporting a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.
  • a further embodiment of the foregoing fixture wherein the fixture defines a first plane with at least three (3) contact points, a second plane with at least two (2) contact points and a third plane with at least one (1) contact point.
  • a further embodiment of any of the foregoing fixtures wherein the clamp portion is supported on the clamp pin and is configured to hold the vane against the clamp pin, the inner locating pin and the outer locating pin.
  • a further embodiment of any of the foregoing fixtures including a fastener for applying a desired pressure to a corresponding one of the plurality of vanes for holding the vane within the defined first, second and third planes.
  • a further embodiment of any of the foregoing fixtures wherein the outer locating pin extends transversely from an outer locating surface and the inner locating pin extends transversely from an inner locating surface and the second plane is defined by the outer and inner locating surfaces adjacent the corresponding inner and outer locating pins.
  • Figure 1 is a schematic view of an example gas turbine engine.
  • Figure 2 is a perspective view of an example stator vane assembly.
  • Figure 3 is a partial schematic view of vanes for the example stator vane assembly.
  • Figure 4 is a perspective view of a top portion of the example stator vane assembly.
  • Figure 5 is a bottom view of the example stator vane assembly.
  • Figure 6 is a top view of a fixture for assembling a stator vane assembly.
  • Figure 7 is a perspective view of an outer portion of the example stator fixture for assembling a stator vane assembly.
  • Figure 8 a is a schematic view of the datum planes established by the example fixture assembly.
  • Figure 8b is a schematic representation of a datum plane established by the example fixture assembly.
  • Figure 9 is an enlarged view of datum planes defined by an outer locating ring.
  • Figure 10 is an enlarged view of data points defined by an example outer locating ring.
  • Figure 11 is an enlarged view of a datum point established by an example clamping section.
  • Figure 12 is a perspective view showing the establishment of another datum point defining a desired datum plane.
  • FIG. 1 schematically illustrates an example gas turbine engine 20 that includes a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flow path B while the compressor section 24 draws air in along a core flow path C where air is compressed and communicated to a combustor section 26.
  • air is mixed with fuel and ignited to generate a high pressure exhaust gas stream that expands through the turbine section 28 where energy is extracted and utilized to drive the fan section 22 and the compressor section 24.
  • turbofan gas turbine engine depicts a turbofan gas turbine engine
  • the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines; for example a turbine engine including a three-spool architecture in which three spools concentrically rotate about a common axis and where a low spool enables a low pressure turbine to drive a fan via a gearbox, an intermediate spool that enables an intermediate pressure turbine to drive a first compressor of the compressor section, and a high spool that enables a high pressure turbine to drive a high pressure compressor of the compressor section.
  • the example engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided.
  • the low speed spool 30 generally includes an inner shaft 40 that connects a fan 42 and a low pressure (or first) compressor section 44 to a low pressure (or first) turbine section 46.
  • the inner shaft 40 drives the fan 42 through a speed change device, such as a geared architecture 48, to drive the fan 42 at a lower speed than the low speed spool 30.
  • the high-speed spool 32 includes an outer shaft 50 that interconnects a high pressure (or second) compressor section 52 and a high pressure (or second) turbine section 54.
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via the bearing systems 38 about the engine central longitudinal axis A.
  • the example gas turbine engine 20 includes a front architecture 62 that includes a plurality of stator vanes 64.
  • the plurality of stator vanes 64 are disposed aft of the fan section 22 and fan blades 42 at the inlet for core air flow C.
  • the plurality of stator vanes 64 are disposed forward of a plurality of inlet guide vanes 66 that are disposed prior to a low pressure compressor 44.
  • the plurality of stator vanes 64 are arranged circumferentially about the engine axis A within the inlet for core engine flow C.
  • stator vanes 64 are part of a stator vane assembly 68 that includes an outer fairing 70 and an inner fairing 72.
  • the plurality of stator vanes 64 extend between the inner fairing 72 and the outer fairing 70.
  • stator vanes 64 are supported within openings or slots 74 defined within each of the inner and outer fairings 72, 70.
  • Each of the stator vanes 64 includes an inner end 80, an outer end 82, a leading edge 84 and a trailing edge 86.
  • Each of the stator vanes 64 are supported within the openings 74 by a sealant 76.
  • the example sealant 76 is a curable material that remains flexible once cured.
  • the stator vanes 64 are mounted within the openings 74 by way of the curable sealant material 76.
  • the sealant 76 provides a bonded joint between the inner and outer fairings 70, 72 and is injected into the openings and within gaps between each of the vanes 64 and the corresponding slot 74 to vibrationally isolate the outer and inner fairings 70, 72 from the stator vanes 64.
  • Each of the stator vanes 64 include tabs 78 that secured the vane 64 within the outer fairing 70 and prevents it from sliding through the opening 74. However, it is the sealant 76 that provides the joint that maintains each of the vanes 64 in a desired position relative to the other vanes 64 and each of the outer and inner fairings 70, 72. Assembly of the stator vane assembly 68 requires specific positioning of each of the vanes 64 within corresponding openings 74. Positioning within the openings 74 is provided such that the vanes 64 themselves do not engage the outer and inner fairings 70, 72. An assembly fixture is utilized to define and maintain a relative position between the plurality of stator vanes 64 and the outer and inner fairings 70, 72 while the sealant 76 is applied and cured to form the completed stator vane assembly 68.
  • an example disclosed assembly fixture 88 includes a base 90 that supports the outer fairing 70 and the inner fairing 72 along with the plurality of stator vanes 64 in a desired position for assembly including the application and curing of the sealant 76 ( Figures 4 and 5).
  • the example assembly fixture 88 defines the specific datum planes and points required to properly align each of the plurality of vanes 64 relative to adjacent vanes and the outer and inner and fairings 70, 72.
  • the example fixture assembly 88 includes the base 90 that holds clamps 114 that are provided to hold the outer fairing 70 in place.
  • the base 90 also includes pins 124 that align with openings within the fairing 70 to align the outer fairing 70.
  • An outer locating ring 92 includes a plurality of locating pins 94 disposed radially inward of the mounted outer fairing 70.
  • An inner locating ring 96 is disposed radially inward of the outer locating ring 92 and includes inner locating pin 98.
  • a clamp section 104 is disposed between the inner and outer locating rings 96, 92 and includes a clamp portion 106 supported on a clamp pin 108.
  • the inner fairing 72 is supported on an inner portion of the base 90 and held in place by inner clamps 116. Similarly, the outer fairing 70 is held in place by outer clamps 114.
  • the inner locating ring 92 and the outer rotating ring 92 includes surfaces 100, 102 that support the vane 64 within the openings 74.
  • FIGS 8 a and 8b With continued reference to Figures 6 and 7, the inner and outer locating rings 96, 92 along within the clamp section 104 define three datum planes for each vane 64 relative to the outer and inner fairings 70, 72.
  • Figures 8a and 8b are schematic representations illustrating the planes utilized to align the vanes 64 relative to the fairings 70, 72.
  • a first plane 118 is defined along a surface of the vane 64 that is transverse to a surface of the base 90.
  • a second plane 120 ( Figure 8B) is defined along the base 90 and along the surfaces 100 and 102 of the inner and outer locating rings 96, 92.
  • a third datum plane 122 is defined at the radially inner most position and sets a radial position of the vane 64.
  • the first plane 118 is defined by the inner locating pin 98, the outer locating pin 94 and a clamp post 108.
  • Each of the inner pin 98, the outer pin 94, and the clamp post 108 defines a point along the first plane 118.
  • the inner locating pin 98 defines a point 128.
  • the outer locating pin 94 defines another point 130 between the pin 94 and the vane 64.
  • the clamp post 108 defines a third locating point 132 between the post 108 and the vane 64.
  • the second plane 120 ( Figure 8b) is defined by the surface 100 of the outer locating ring 92 and the surface 102 of the inner locating ring 92.
  • the surfaces 100 and 102 are disposed adjacent the corresponding locating pin 94, 98.
  • the radial position defined as plane 122 is defined by the radial pin 140 that abuts the inner end 80 of the vane 64.
  • the example fixture 88 includes the inner locating ring 96 that includes the surface 102 and the locating pin 98.
  • the surface 102 defines the locating point 134 for the second plane 120.
  • the locating pin 98 defines the first point 128 along the plane 118.
  • the vane 64 is abutted against the pin 98 and the bottom surface 102 to set one point along the first plane 118 and the second plane 120.
  • the outer locating ring 92 includes the surface 100 and the locating pin 94.
  • the vane 64 is abutted against the surface 100 and the pin 94.
  • the pin 94 defines the locating point 130 that is a second point along the plane 118.
  • the outer ring surface 100 defines another point 136 that defines a second point along the plane 120.
  • a third point along the plane 118 is defined by the clamp post 108.
  • the example clamp section 104 includes the clamp post 108 that extends upwardly from the base 90.
  • the example clamp post 108 includes a point 132 onto which the vane 64 comes into contact.
  • the example point 132 defines a third point along the plane 118.
  • the example vane 64 abuts the outer locating pin 94, the inner locating pin 98, and the clamp pin 108 to define the first plane 118.
  • the first plane 118 includes a specific orientation of the vane 64 that corresponds with the aerodynamic shape of the vane 64.
  • the clamp section 104 holds and defines an angular orientation of each of the plurality of vanes 64 relative to each of the outer and inner fairings70, 72.
  • the clamp post 108 that supports a surface of the vane 64 and also a clamp portion 106 including a clamp surface 112 that engages an opposite end of the vane 64 and is utilized to hold the vane 64 in contact with the clamp post 108 and the locating pins 94 and 98.
  • each of the vanes 64 is defined by radial locating pins 140 within the radial positioning section 142.
  • An inner end 80 of each of the vanes 64 engages the surface of each of the corresponding radial locator pins 140 to define and set a desired radial position of each of the vanes 64 in relation to the corresponding outer and inner fairings 70, 72.
  • Figure 12 further shows a top view of the clamp section 104 where the clamp portions 106 are held to a corresponding clamp post 108 by a clamp fastener 110.
  • Each of the clamp fasteners 110 provides for securement of the corresponding vane 64 independent of the other vanes 64.
  • the example fixture 88 is utilized to define the relative position between the outer and inner fairings 70, 72 prior to application of the sealant 76.
  • the individual vanes 64 are inserted into the fixture 88 after the corresponding outer and inner fairings 70, 72 are mounted to the base plate 90.
  • the outer and inner and outer fairings 70, 72 are aligned on the base plate 90 utilizing the locating pins 124 and 126.
  • each of the plurality of vanes 64 is inserted into the fixture 88.
  • the vanes 64 are inserted through the opening 74 within the outer fairing 70 radially inward until abutting the radial locating pin 40.
  • the clamp portion 106 of the clamp section 104 is secured to bias and hold the vane 64 against the locating pins 98 and 94 on corresponding inner and outer locating rings 92, 96.
  • the clamp portion 106 also secures and holds the vane assembly 64 against the corresponding inner locating ring surface 100 and outer locating surface 102.
  • the sealant 76 can be applied to the gaps between each of the vanes 64 and the corresponding fairings 70. 72.
  • the sealant 76 is applied within the gap to secure the vane 64 within the outer and inner fairings 70, 72 and also to eliminate vibratory transmission between parts.
  • the example fixture 88 is comprised of a material compatible with the conditions utilized for curing the sealant 76 within the openings 74. Once the sealant 76 has properly cured the stator vane assembly 68 can be removed from the fixture 88. Removal of the vane assembly from the fixture includes removal of the clamp portions 106 from the clamp section 104. Once the clamp portions 106 are removed, the outer clamps 114 and the inner clamps 116 can be removed to allow the completed stator vane assembly 68 to be lifted upwardly off of the base plate 90.
  • the example fixture 88 provides for the specific positioning of each of a plurality of vanes 64 relative to the outer and inner fairings 70, 72 such that sealant 76 can be applied to hold each of the vanes 64 within the assembly. Further, the example fixture 88 defines the specific datum points and planes that are utilized to align each of the vanes 64 relative to adjacent vanes 64 and the outer and inner fairings 70, 72.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur un dispositif servant à assembler un ensemble aube de stator pour un moteur à turbine à gaz, qui comprend un anneau de positionnement extérieur, comprenant une pluralité de goupilles de positionnement extérieur définissant une position pour chacune d'une pluralité d'aubes par rapport à un carénage extérieur, et un anneau de positionnement intérieur, comprenant une pluralité d'anneaux de positionnement intérieur définissant une position de chacune de la pluralité d'aubes par rapport à un carénage intérieur. Une section de pince comprend une partie pince et une goupille de pince qui définissent une orientation angulaire de chacune de la pluralité d'aubes par rapport à chacun des carénages intérieur et extérieur, et une section de positionnement intérieur qui supporte une pluralité de goupilles de positionnement radial définissant une position radiale de chacune de la pluralité d'aubes par rapport aux carénages intérieur et extérieur.
EP13796412.8A 2012-05-30 2013-05-08 Dispositif d'assemblage pour un ensemble aube de stator Active EP2859189B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/483,501 US8966755B2 (en) 2011-01-20 2012-05-30 Assembly fixture for a stator vane assembly
PCT/US2013/040042 WO2013180916A1 (fr) 2012-05-30 2013-05-08 Dispositif d'assemblage pour un ensemble aube de stator

Publications (3)

Publication Number Publication Date
EP2859189A1 true EP2859189A1 (fr) 2015-04-15
EP2859189A4 EP2859189A4 (fr) 2016-08-24
EP2859189B1 EP2859189B1 (fr) 2017-12-27

Family

ID=49673815

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13796412.8A Active EP2859189B1 (fr) 2012-05-30 2013-05-08 Dispositif d'assemblage pour un ensemble aube de stator

Country Status (2)

Country Link
EP (1) EP2859189B1 (fr)
WO (1) WO2013180916A1 (fr)

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2728016B1 (fr) * 1994-12-07 1997-01-17 Snecma Distributeur monobloc non-sectorise d'un stator de turbine de turbomachine
US6164903A (en) * 1998-12-22 2000-12-26 United Technologies Corporation Turbine vane mounting arrangement
US6343912B1 (en) * 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame
GB2427900B (en) * 2005-07-02 2007-10-10 Rolls Royce Plc Vane support in a gas turbine engine
US7178255B1 (en) * 2005-09-09 2007-02-20 General Electric Company Methods and apparatus for manufacturing components
US8092157B2 (en) * 2007-12-19 2012-01-10 United Technologies Corporation Variable turbine vane actuation mechanism having a bumper ring
US8511983B2 (en) * 2008-02-19 2013-08-20 United Technologies Corporation LPC exit guide vane and assembly
CA2682818A1 (fr) 2009-10-15 2011-04-15 General Electric Company Methode de realisation de carenage avec diaphragme obturateur integre
EP2312186A1 (fr) 2009-10-16 2011-04-20 General Electric Company Procédé de fabrication d'un carénage avec une étanchéité intégrée
US8533947B2 (en) * 2010-10-28 2013-09-17 Pcc Airfoils, Inc. Method of forming a turbine engine component
US8668448B2 (en) 2010-10-29 2014-03-11 United Technologies Corporation Airfoil attachment arrangement

Also Published As

Publication number Publication date
EP2859189A4 (fr) 2016-08-24
WO2013180916A1 (fr) 2013-12-05
EP2859189B1 (fr) 2017-12-27

Similar Documents

Publication Publication Date Title
US9567863B2 (en) Assembly fixture for a stator vane assembly
US9121283B2 (en) Assembly fixture with wedge clamps for stator vane assembly
US9731388B2 (en) Method and fixture for airfoil array assembly
US20130104398A1 (en) Rotor blade assembly tool for gas turbine engine
US10727656B2 (en) Igniter cable conduit for gas turbine engine
US20140227078A1 (en) Mid-turbine frame vane assembly support with retention unit
EP2901083B1 (fr) Ensemble combusteur de turbine à gaz et procédé d'assemblage d'un tel ensemble
EP3187686A1 (fr) Procédé et système de clip de retenue de plate-forme d'aube séparable
EP2880282B1 (fr) Ensemble compresseur avec ergot anti-rotation de stator
EP2865847A1 (fr) Procédé et appareil pour supporter des aubes
US20150218966A1 (en) Gas turbine engine fan spacer platform attachments
EP2859189B1 (fr) Dispositif d'assemblage pour un ensemble aube de stator
EP2971578B1 (fr) Procédé d'assemblage d'une structure avant de moteur à turbine à gaz et structure avant de moteur à turbine à gaz associée
EP3611359A1 (fr) Bague à cannelure pour un support flexible d'engrenage d'entraînement de soufflante
US10167737B2 (en) Structural guide vane circumferential load bearing shear pin
EP3517735A1 (fr) Ensemble aube de stator de moteur de turbine à gaz
EP3404215A1 (fr) Antirotation de joint d'étanchéité
US20150121682A1 (en) Extraction tool assembly
US11021970B2 (en) Turbomachine with alternatingly spaced rotor blades
US20210123355A1 (en) System for an improved stator assembly
US20200063590A1 (en) Sealing member for gas turbine engine
US20160017742A1 (en) Brush seal repair method

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

17P Request for examination filed

Effective date: 20141113

AK Designated contracting states

Kind code of ref document: A1

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

DAX Request for extension of the european patent (deleted)
RA4 Supplementary search report drawn up and despatched (corrected)

Effective date: 20160722

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 9/04 20060101ALI20160718BHEP

Ipc: F02C 7/00 20060101ALI20160718BHEP

Ipc: F01D 25/28 20060101ALI20160718BHEP

Ipc: F01D 5/00 20060101ALI20160718BHEP

Ipc: F01D 9/00 20060101AFI20160718BHEP

Ipc: F01D 9/02 20060101ALI20160718BHEP

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

Owner name: UNITED TECHNOLOGIES CORPORATION

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20170719

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 958485

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602013031427

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180327

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20171227

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 958485

Country of ref document: AT

Kind code of ref document: T

Effective date: 20171227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180328

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180327

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180427

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013031427

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

26N No opposition filed

Effective date: 20180928

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180531

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180508

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180508

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180508

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171227

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20130508

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602013031427

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240418

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240418

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240418

Year of fee payment: 12