US20130004314A1 - Radial spline arrangement for lpt vane clusters - Google Patents

Radial spline arrangement for lpt vane clusters Download PDF

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Publication number
US20130004314A1
US20130004314A1 US13/172,279 US201113172279A US2013004314A1 US 20130004314 A1 US20130004314 A1 US 20130004314A1 US 201113172279 A US201113172279 A US 201113172279A US 2013004314 A1 US2013004314 A1 US 2013004314A1
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United States
Prior art keywords
vane
case
splines
spline
gas turbine
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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.)
Abandoned
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US13/172,279
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English (en)
Inventor
Ioannis Alvanos
Gabriel L. Suciu
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RTX Corp
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United Technologies Corp
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Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to US13/172,279 priority Critical patent/US20130004314A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ALVANOS, IOANNIS, SUCIU, GABRIEL
Priority to EP12169688.4A priority patent/EP2540983A3/fr
Publication of US20130004314A1 publication Critical patent/US20130004314A1/en
Abandoned legal-status Critical Current

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    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates generally to gas turbine engines, and more particularly to the attachment of a full hoop stator vane cluster to a case of a gas turbine engine.
  • a gas turbine engine typically includes a high pressure spool, a combustion system and a low pressure spool disposed within an engine case to form a generally axial, serial flow path about the engine centerline.
  • the high pressure spool includes a high pressure turbine, a high pressure shaft extending axially forward from the high pressure turbine, and a high pressure compressor connected to a forward end of the high pressure shaft.
  • the low pressure spool includes a low pressure turbine, which is disposed downstream of the high pressure turbine, a low pressure shaft, which typically extends coaxially through the high pressure shaft, and a low pressure compressor connected to a forward end of the low pressure shaft, forward of the high pressure compressor.
  • the combustion system is disposed between the high pressure compressor and the high pressure turbine and receives compressed air from the compressors and fuel provided by a fuel injection system.
  • a combustion process is carried out within the combustion system to produce high energy gases to produce thrust and turn the high and low pressure turbines, which drive the compressors to sustain the combustion process.
  • Turbines are comprised of alternating stages of blades and airfoils that are arranged radially around a center axis of the engine within the axial flow path of the engine case. More specifically, the blades are attached to a support rotor and the airfoils are attached to the engine case. When high energy gases pass through a turbine, heat is transferred to the airfoils and the case. Due to local gas flow paths and component features and geometry, thermal expansion is not equal over the entire turbine section. Similarly, the case and the airfoils may not expand equally during operation and contract equally after operation. This phenomenon can cause thermal stresses and crack formation that can lead to failure of the components.
  • a full hoop stator vane cluster includes an inner hoop and an outer hoop both being substantially cylindrical and coaxial.
  • a plurality of airfoils extend radially between the hoops, and a plurality of vane splines extend radially outward from the outer hoop for attaching the vane cluster to a gas turbine engine.
  • a gas turbine engine in another embodiment, includes a full hoop stator vane cluster and a case.
  • the full hoop stator vane cluster includes an inner hoop and an outer hoop both being substantially cylindrical and coaxial.
  • a plurality of airfoils extend radially between the hoops, and a plurality of vane splines extend radially outward from the outer hoop for attaching the vane cluster to a gas turbine engine.
  • the case is substantially cylindrical and has a plurality of case splines extending radially inward for attaching the vane cluster.
  • a method of installing a full hoop stator vane cluster into a gas turbine engine includes inserting the vane cluster axially into a case of the gas turbine engine. Also included are moving a plurality of vane splines on the vane cluster alongside a plurality of case splines on the case and circumferentially offsetting the vane splines and the case splines. Further included are rotating the vane cluster such that the vane splines are circumferentially aligned with the case splines and attaching a vane spline to a case spline to substantially restrain relative axial and circumferential movement.
  • FIG. 1 is a schematic cross-section view of a gas turbine engine showing a vane cluster.
  • FIG. 2 is a perspective view of the vane cluster showing vane splines.
  • FIG. 3A is a partial perspective view of the vane cluster and a low pressure turbine case.
  • FIG. 3B is a partial perspective view of the vane cluster attached to the low pressure turbine case.
  • FIG. 4 is a partial cross-section view along line 3 in FIG. 1 showing the vane cluster attached to the low pressure turbine case.
  • FIG. 5 is a perspective view of a vane cluster having alternate embodiment vane splines and a low pressure turbine case having alternate embodiment case splines.
  • FIG. 1 shows a cross section of gas turbine engine 10 in which a vane cluster of the present invention is used.
  • FIG. 1 depicts a gas turbine engine typically used for aircraft propulsion, the invention is readily applicable to gas turbine generators and other similar systems incorporating rotor-supported, shaft-driven turbines. Shown in FIG.
  • gas turbine engine 10 gas turbine engine 10 , fan 12 , low pressure compressor (LPC) 14 , high pressure compressor (HPC) 16 , combustor section 18 , high pressure turbine (HPT) 20 , low pressure turbine (LPT) 22 , fan case 23 A, LPC case 23 B, HPC case 23 C, HPT case 23 D, LPT case 23 E, shaft 24 , shaft 26 , exit guide vanes 28 , injectors 30 , blades 32 , vane clusters 34 , airfoils 36 , support rotor 38 , inlet air A, primary air A P , secondary air A S , and longitudinal engine centerline axis C L .
  • gas turbine engine 10 comprises a dual-spool turbofan engine in which the advantages of the present invention are particularly well illustrated.
  • Gas turbine engine 10 of which the operational principles are well known in the art, comprises fan 12 , low pressure compressor (LPC) 14 , high pressure compressor (HPC) 16 , combustor section 18 , high pressure turbine (HPT) 20 , and low pressure turbine (LPT) 22 , which are each concentrically disposed around longitudinal engine centerline axis C L .
  • Fan 12 is enclosed at its outer diameter within fan case 23 A.
  • the other engine components are correspondingly enclosed at their outer diameters within various engine casings, including LPC case 23 B, HPC case 23 C, HPT case 23 D (including the mid-turbine frame), and LPT case 23 E.
  • Fan 12 and LPC 14 are connected to LPT 22 through shaft 24 , and together fan 12 , LPC 14 , LPT 22 , and shaft 24 comprise the low pressure spool.
  • HPC 16 is connected to HPT 20 through shaft 26 , and together HPC 16 , HPT 20 , and shaft 26 comprise the high pressure spool.
  • Inlet air A enters engine 10 where it is divided into streams of primary air A P and secondary air A S after passing through fan 12 .
  • Fan 12 is rotated by low pressure turbine 22 through shaft 24 (either directly as shown or through a gearbox, not shown) to accelerate secondary air A S (also known as bypass air) through exit guide vanes 28 , thereby producing a major portion of the thrust output of engine 10 .
  • Primary air A P (also known as gas path air) is directed first into low pressure compressor 14 and then into high pressure compressor 16 .
  • LPC 14 and HPC 16 work together to incrementally step up the pressure of primary air A.
  • HPC 16 is rotated by HPT 20 through shaft 24 to provide compressed air to combustor section 18 .
  • the compressed air is delivered to combustor 18 , along with fuel through injectors 30 , such that a combustion process can be carried out to produce the high energy gases necessary to turn high pressure turbine 20 and low pressure turbine 22 , which is comprised of blades 32 and vane clusters 34 (which includes airfoils 36 ).
  • Primary air A P continues through gas turbine engine 10 whereby it is typically passed through an exhaust nozzle to further produce thrust.
  • engine 10 can be a three spool engine.
  • engine 10 has an intermediate compressor between LPC 14 and HPC 16 and an intermediate turbine between HPT 20 and LPT 22 , wherein the intermediate compressor is connected to the intermediate turbine with an additional shaft.
  • FIG. 2 a perspective view of vane cluster 34 having vane splines 40 is shown. Shown in FIG. 2 are vane cluster 34 , airfoils 36 , inner hoop 42 , outer hoop 44 , cluster axis 46 , and vane prongs 48 and vane slots 50 , which form vane splines 40 .
  • vane cluster 34 airfoils 36 , inner hoop 42 , outer hoop 44 , cluster axis 46 , and vane prongs 48 and vane slots 50 , which form vane splines 40 .
  • some of airfoils 36 and vane splines 40 have been omitted, the omitted portions being indicated by dots.
  • Vane cluster 34 includes substantially cylindrical inner hoop 42 surrounded by substantially cylindrical outer hoop 44 . Vane cluster 34 has cluster axis 46 , to which inner hoop 42 and outer hoop 44 are coaxial. Connected to and extending radially between inner hoop 42 and outer hoop 44 is a plurality of airfoils 36 . Because vane cluster 34 subtends substantially a full cylinder, vane cluster 34 is a full hoop stator vane cluster.
  • each vane spline 40 is comprised of two vane prongs 48 .
  • Vane prongs 48 extend generally radially outward from outer hoop 44 and are substantially parallel to each other. Vane prongs 48 are circumferentially separated from each other by vane slots 50 .
  • Each vane slot 50 is circumferentially wider than each vane prong 48 .
  • Blades 32 are connected to shaft 24 (shown in FIG. 1 ) through support rotor 38 such that they rotate during operation of LPT 22 .
  • Vane cluster 34 remains stationary during operation of LPT 22 . Therefore, airfoils 36 remain stationary during operation of LPT 22 .
  • vane cluster 34 as shown in FIG. 2 allow for vane cluster 34 to be attached to LPT case 23 E (as shown in FIGS. 3A-3B ). More specifically, vane cluster 34 can remain substantially centered in LPT case 23 E despite independent thermal expansion of vane cluster 34 and LPT case 23 E. In addition, vane splines 40 can transmit circumferential force and/or torque to LPT case 23 E. Because vane cluster 34 is a full hoop stator vane cluster, there are no radial gaps to fill between segments (as occur in the prior art).
  • FIG. 3A a partial perspective view of vane cluster 34 and LPT case 23 E is shown.
  • FIG. 3B a partial perspective view of the vane cluster attached to the low pressure turbine case. Shown in FIGS. 3A-3B are LPT case 23 E, vane cluster 34 , vane splines 40 (with vane prongs 48 and vane slots 50 ), case splines 52 (with case prongs 54 and case slots 56 ), and fasteners 58 .
  • LPT case 23 E Shown in FIGS. 3A-3B are shown in FIGS. 3A-3B are LPT case 23 E, vane cluster 34 , vane splines 40 (with vane prongs 48 and vane slots 50 ), case splines 52 (with case prongs 54 and case slots 56 ), and fasteners 58 .
  • FIGS. 3A-3B will occur simultaneously.
  • LPT case 23 E is substantially cylindrical and is coaxial with longitudinal engine centerline axis C L (shown in FIG. 1 ). Attached to and extending substantially radially inward from LPT case 23 E are case splines 52 .
  • each case spline 52 is comprised of two case prongs 54 .
  • Case prongs 54 extend generally radially inward from LPT case 23 E and are substantially parallel to each other.
  • Case prongs 52 are circumferentially separated from each other by case slots 56 .
  • Each case slot 56 is circumferentially wider than each case prong 52 .
  • vane splines 40 and case splines 52 have corresponding shapes, and, more specifically, are substantially the same shape.
  • cluster axis 46 (shown in FIG. 2 ) is oriented to be substantially coaxial with longitudinal engine centerline axis C L (shown in FIG. 1 ) and vane cluster 34 is axially inserted into LPT case 23 E along longitudinal engine centerline axis C L .
  • Vane cluster 34 is axially positioned within LPT case 23 E, with vane splines 40 being positioned circumferentially offset from case splines 52 (as shown in FIG. 3A ). Then vane cluster 34 is rotated about cluster axis 46 (shown in FIG. 2 ) until vane splines 40 and case splines 52 are circumferentially aligned (as shown in FIG.
  • vane slots 50 and case slots 56 are axially aligned.
  • fasteners 58 are added to attach vane cluster 34 to LPT case 23 E. More specifically, one fastener 58 is axially inserted into each vane slot 50 and case slot 56 , between vane prongs 48 and case prongs 54 of vane spline 40 and case spline 52 , respectively.
  • vane cluster 34 may need to be moved axially past case splines 52 (as will be discussed in greater detail with FIG. 4 ). Therefore, the circumferential spacing between each vane spline 40 and the circumferential spacing between each case spline 52 allow for vane cluster 34 to be moved axially past case splines 52 without interfering with any features of LPT case 23 E. More specifically, the amount of circumferential space between any two consecutive vane splines 40 is greater than the circumferential width of an individual case spline 52 .
  • the amount of circumferential space between any two consecutive case splines 52 is greater than the circumferential width of an individual vane spline 40 . Because the width of each vane spline 40 is substantially the same as the width of each case spline 52 in the illustrated embodiment, the result is that the circumferential spacing between vane splines 40 and case splines 52 is substantially the same. This also means that the amount of circumferential space between any two consecutive vane splines 40 is greater than the circumferential width of an individual vane spline 40 . Similarly, the amount of circumferential space between any two consecutive vane splines 52 is greater than the circumferential width of an individual case spline 52 .
  • vane cluster 34 and LPT case 23 E allow for vane cluster 34 to be attached to LPT case 23 E. Because fasteners 58 are positioned in vane slots 50 and case slots 56 , relative movement between vane cluster 34 and LPT case 23 is substantially prohibited in the axial and circumferential directions. Relative movement is permitted in the radial direction. In addition, vane cluster 34 can be moved past case splines 52 , which allows for the assembly of a multi-stage LPT 22 (shown in FIG. 1 ).
  • FIG. 4 a partial cross-section view along line 4 in FIG. 1 of vane cluster 34 attached to LPT case 23 E is shown. Shown in FIG. 4 are LPT case 23 E, vane cluster 34 , support rotor 38 , vane spline 40 , outer hoop 44 , case splines 52 , fastener 58 , knife edge seals 60 , and abradable 62 .
  • Vane cluster 34 and LPT case 23 E are as described previously in FIGS. 1-3B , with additional detail shown in FIG. 4 .
  • LPT case 23 E has, but is not limited to, two sets of case splines 52 that are axially spaced apart from one another.
  • vane splines 40 are moved between the two sets of case splines 52 .
  • LPT case 23 E and vane cluster 34 as shown in FIG. 4 allow for vane splines 40 to be attached in double shear. Also, as stated previously, relative movement between vane cluster 34 and LPT case 23 E is permitted in the radial direction, though it is limited by the outer ends of vane prongs 48 contacting LPT case 23 and/or the inner ends of case prongs 54 contacting outer hoop 44 . This contact will prevent knife edge seals 60 on support rotor 38 from moving extensively into abradable 62 . More specifically, vane prong 48 and/or case prong 54 contact on one side of gas turbine engine 10 (shown in FIG. 1 ) prevents knife edge seals 60 on the opposite side from bearing load. This can be especially useful when gas turbine engine 10 is at rest.
  • FIG. 5 a perspective view of vane cluster 34 having alternate embodiment vane splines 40 ′ and LPT case 23 E having alternate embodiment case splines 52 ′ is shown. Shown in FIG. 5 are LPT case 23 E, vane cluster 34 , vane splines 40 ′, vane prongs 48 ′, vane slots 50 ′, case splines 52 ′, case prongs 54 ′, and case slots 56 ′.
  • vane splines 40 ′ each pair of vane prongs 48 ′ are joined at the outermost ends of vane prongs 48 ′. Thereby, vane slots 50 ′ are surrounded by a closed ring comprised of vane prongs 48 ′.
  • case splines 52 ′ each pair of case prongs 54 ′ are joined at the innermost ends of case prongs 54 ′.
  • case slots 56 ′ are surrounded by a closed ring comprised of case prongs 56 ′.
  • vane splines 40 ′ and case splines 52 ′ are substantially the same shape.
  • case splines 52 ′ can be of a corresponding shape to vane splines 40 ′, such that case slots 56 ′ can align with vane slots 50 ′ (for example, case splines 52 as shown in FIG. 3A ).
  • vane splines 40 ′ can be of a corresponding shape to case splines 52 ′, such that vane slots 50 ′ align with case slots 56 ′ (for example, vane splines 40 as shown in FIG. 3A ).
  • LPT case 23 E and vane cluster 34 can independently thermally expand during operation of gas turbine engine 10 .
  • LPT case 23 E and vane cluster 34 can independently thermally contract.
  • vane splines 40 and/or case splines 52 can bear the weight of vane cluster 34 . This prevents knife edge seals 60 from being crushed by the radially movable vane cluster 34 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/172,279 2011-06-29 2011-06-29 Radial spline arrangement for lpt vane clusters Abandoned US20130004314A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US13/172,279 US20130004314A1 (en) 2011-06-29 2011-06-29 Radial spline arrangement for lpt vane clusters
EP12169688.4A EP2540983A3 (fr) 2011-06-29 2012-05-28 Agencement de cannelures radiales pour un segment des aubes de guidage dans une turbine à basse pression

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US13/172,279 US20130004314A1 (en) 2011-06-29 2011-06-29 Radial spline arrangement for lpt vane clusters

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10822980B2 (en) 2013-04-11 2020-11-03 Raytheon Technologies Corporation Gas turbine engine stress isolation scallop

Citations (4)

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Publication number Priority date Publication date Assignee Title
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
US5839878A (en) * 1996-09-30 1998-11-24 United Technologies Corporation Gas turbine stator vane
US7063505B2 (en) * 2003-02-07 2006-06-20 General Electric Company Gas turbine engine frame having struts connected to rings with morse pins
US20080145217A1 (en) * 2006-12-19 2008-06-19 United Technologies Corporation Method for securing a stator assembly

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4274805A (en) * 1978-10-02 1981-06-23 United Technologies Corporation Floating vane support
US4668164A (en) * 1984-12-21 1987-05-26 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US5289677A (en) * 1992-12-16 1994-03-01 United Technologies Corporation Combined support and seal ring for a combustor
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly
US7025563B2 (en) * 2003-12-19 2006-04-11 United Technologies Corporation Stator vane assembly for a gas turbine engine
US7726937B2 (en) * 2006-09-12 2010-06-01 United Technologies Corporation Turbine engine compressor vanes

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5839878A (en) * 1996-09-30 1998-11-24 United Technologies Corporation Gas turbine stator vane
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
US7063505B2 (en) * 2003-02-07 2006-06-20 General Electric Company Gas turbine engine frame having struts connected to rings with morse pins
US20080145217A1 (en) * 2006-12-19 2008-06-19 United Technologies Corporation Method for securing a stator assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10822980B2 (en) 2013-04-11 2020-11-03 Raytheon Technologies Corporation Gas turbine engine stress isolation scallop

Also Published As

Publication number Publication date
EP2540983A3 (fr) 2018-01-03
EP2540983A2 (fr) 2013-01-02

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Effective date: 20110628

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