EP3650637A1 - Gas turbine vane stage with half vanes integral with an outer case and an inner shroud - Google Patents
Gas turbine vane stage with half vanes integral with an outer case and an inner shroud Download PDFInfo
- Publication number
- EP3650637A1 EP3650637A1 EP19195967.5A EP19195967A EP3650637A1 EP 3650637 A1 EP3650637 A1 EP 3650637A1 EP 19195967 A EP19195967 A EP 19195967A EP 3650637 A1 EP3650637 A1 EP 3650637A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ringcase
- inner shroud
- aft
- trunnion
- stationary half
- 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
Links
- 238000005304 joining Methods 0.000 claims description 19
- 239000007789 gas Substances 0.000 description 21
- 230000000712 assembly Effects 0.000 description 6
- 238000000429 assembly Methods 0.000 description 6
- 238000005452 bending Methods 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000003491 array Methods 0.000 description 2
- 239000003562 lightweight material Substances 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
-
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- 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
Definitions
- Gas turbine engines typically include a compressor section, a combustor section, and a turbine section. During operation, air is pressurized in the compressor section, and is mixed with fuel and burned in the combustor section to generate hot combustion gases. The hot combustion gases are communicated through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads.
- both the compressor and turbine sections include alternating arrays of vanes and rotating blades that extend into a core airflow path of the gas turbine engine.
- compressor blades rotate to pull air into the compressor section for compression.
- the compressor vanes guide the airflow between different arrays (also called stages) of rotating blades and prepare the airflow for a downstream array of blades.
- Some compressor sections include variable area vanes, which include vanes that are moveable to vary the area or direction of the flow of the core airflow path between two stages of rotating blades. Movement of the variable area vanes is controlled to optimize the performance of the gas turbine engine during various operating conditions.
- a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage.
- the ringcase extends completely about the center axis to form a first ring.
- An inner shroud extends circumferentially about the center axis of the vane stage.
- the inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis.
- a plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
- a vane stage in another aspect of the disclosure, includes a ringcase extending circumferentially about a center axis of the vane stage.
- the ringcase extends completely about the center axis to form a first non-segmented ring.
- An inner shroud extends circumferentially about the center axis of the vane stage.
- the inner shroud extends completely about the center axis to form a second non-segmented ring radially within the ringcase relative the center axis.
- a plurality of stationary half vanes extend radially between the ringcase and the inner shroud.
- the plurality of stationary half vanes are circumferentially spaced about the center axis and are integrally connected to the ringcase and the inner shroud.
- Each of the plurality of stationary half vanes includes both a leading edge extending radially from the inner shroud to the ringcase, and a groove extending radially from the inner shroud to the ringcase aft of the leading edge.
- a partial suction surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove.
- a partial pressure surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove opposite the partial suction surface.
- the groove is positioned between the partial suction surface and the partial pressure surface.
- a vane stage in another aspect of the disclosure, includes a ringcase extending circumferentially about a center axis of the vane stage.
- the ringcase extends completely about the center axis to form a first non-segmented ring.
- An inner shroud extends circumferentially about the center axis of the vane stage.
- the inner shroud extends completely about the center axis to form a second non-segmented ring positioned radially within the ringcase relative the center axis.
- a plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
- a plurality of trunnion holes are formed in the ringcase aft of the plurality of stationary half vanes. Each trunnion hole of the plurality of trunnion holes is circumferentially aligned with one of the plurality of stationary half vanes and extends radially through the ringcase.
- the present disclosure provides a vane stage with an integral half vane structure with an outer ringcase, an inner shroud, and a plurality of stationary half vanes.
- Rotating variable half vanes are assembled onto the integral half vane structure aft of the stationary half vanes.
- the stationary half vanes and the variable half vanes form an array of vanes where each vane has a fixed leading edge and an adjustable trailing edge that can be controlled to optimize the performance of a gas turbine engine during various operating conditions. Because the plurality of stationary half vanes, the outer ringcase and the inner shroud are integral, the position of stationary half vanes within integral half vane structure can be tightly controlled, which leads to tighter tolerances between the stationary half vanes and the variable half vanes.
- FIG. 1 is a quarter-sectional view that schematically illustrates example gas turbine engine 20 that includes fan section 22, compressor section 24, combustor section 26 and turbine section 28.
- Fan section 22 drives air along bypass flow path B in bypass duct D while compressor section 24 draws air in along core flow path C where air is compressed and communicated to combustor section 26.
- combustor section 26 air is mixed with fuel and ignited to generate a high pressure exhaust gas stream that expands through turbine section 28 where energy is extracted and utilized to drive fan section 22 and compressor section 24.
- the disclosed non-limiting embodiment depicts a turbofan gas turbine engine, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.
- the example gas turbine engine 20 generally includes low speed spool 30 and high speed spool 32 mounted for rotation about center axis CA of gas turbine engine 20 relative to engine static structure 36 via several bearing assemblies 38. It should be understood that various bearing assemblies 38 at various locations may alternatively or additionally be provided.
- Low speed spool 30 generally includes inner shaft 40 that connects fan 42 and low pressure (or first) compressor 44 to low pressure (or first) turbine 46.
- Inner shaft 40 drives fan 42 through a speed change device, such as geared architecture 48, to drive fan 42 at a lower speed than low speed spool 30.
- High-speed spool 32 includes outer shaft 50 that interconnects high pressure (or second) compressor 52 and high pressure (or second) turbine 54.
- Inner shaft 40 and outer shaft 50 are concentric and rotate via bearing assemblies 38 about center axis CA.
- Combustor 56 is arranged between high pressure compressor 52 and high pressure turbine 54.
- Mid-turbine frame 57 of engine static structure 36 can be arranged generally between high pressure turbine 54 and low pressure turbine 46.
- Mid-turbine frame 57 further supports bearing assemblies 38 in turbine section 28 as well as setting airflow entering the low pressure turbine 46.
- Mid-turbine frame 57 includes airfoils 59 which are in core flow path C. The air in core flow path C is compressed first by low pressure compressor 44 and then by high pressure compressor 52. Next, the air is mixed with fuel and ignited in combustor 56 to produce high speed exhaust gases that are then expanded through high pressure turbine 54, mid-turbine frame 58, and low pressure turbine 46.
- compressor section 24 can include an integral half vane structure 60 that is used in a variable vane stage.
- FIG. 2 is a perspective view of integral half vane structure 60.
- FIG. 3 is a perspective cross-sectional view of integral half vane structure 60 with the cross section taken in the axial-radial plane.
- FIG. 4 is a perspective cross-sectional view of integral half vane structure 60 with the cross section taken in the axial-circumferential plane.
- integral half vane structure 60 includes ringcase 62, inner shroud 64, and a plurality of stationary half vanes 66.
- integral half vane structure 60 also includes forward flange 68 and aft flange 70 on ring case 62, and mounting tabs 72 on inner shroud 64.
- each stationary half vane 66 in the plurality of half vanes 66 includes leading edge 74, groove 76, partial suction surface 78, and partial pressure surface 80.
- Inner shroud includes forward edge 82, aft edge 84, and a plurality of sockets 86.
- Ringcase 62 includes forward edge 88, aft edge 90 (shown in FIG. 2 ), and a plurality of outer trunnion holes 92.
- each stationary half vane 66 can also include undercut 94. Aft ring 96 and inner trunnion holes 98 are also shown in FIG. 4 .
- Ringcase 62 extends circumferentially about center axis CA. Ringcase 62 extends completely about center axis CA to form a first complete and non-segmented ring. Ringcase 62 extends axially from forward edge 88 to aft edge 90. Forward flange 68 is formed on forward edge 88 of ringcase 62 and extends radially outward from ringcase 62. Aft flange 70 is formed on aft edge 90 of ringcase 62 and extends radially outward from ringcase 62. Forward flange 68 and aft flange 70 are configured to allow ringcase 62 to be mounted between two axially-adjacent structures (not shown) in gas turbine engine 20.
- Inner shroud 64 also extends circumferentially about center axis CA. Similar to ringcase 62, inner shroud 64 extends completely about center axis CA to form a second complete and non-segmented ring. Inner shroud 64 is smaller in diameter than ringcase 62 and is positioned radially within ringcase 62 such that ringcase 62 and inner shroud 64 are concentric on central axis CA. Inner shroud 64 extends axially from forward edge 82 to aft edge 84. Mounting tabs 72 are formed on a radially inner surface of inner shroud 64 between forward edge 82 and aft edge 84.
- Mounting tabs 72 are circumferentially spaced from one another and extend radially inward from inner shroud 64. Mounting tabs 72 are provided to connect inner shroud 64 to forward and aft adjacent structures (such as aft ring 96 shown in FIG. 5 ) in gas turbine engine 20.
- the plurality of stationary half vanes 66 extend radially between ringcase 62 and inner shroud 64 and connect ringcase 62 and inner shroud 64 together.
- Stationary half vanes 66 are spaced circumferentially about center axis CA.
- Stationary half vanes 66 are integral with ring case 62 and inner shroud 64.
- Integral half vane structure 60 can be formed by machining ringcase 62, inner shroud 64 and stationary half vanes 66 from a single piece of metal. Integral half vane structure 60 can also be made by first forming ringcase 62, welding a cylindrical plate (not shown) inside ringcase 62, and machining the cylindrical plate to form inner shroud 64 and stationary half vanes 66.
- Integral half vane structure 60 can also be made by separately forming ringcase 62, inner shroud 64, and stationary half vanes 66, and welding ringcase 62, inner shroud 64, and stationary half vanes 66 together. Integral half vane structure 60 can also be formed through additive manufacturing.
- leading edge 74 of each stationary half vane 66 extends radially from inner shroud 64 to ringcase 62.
- the body of stationary half vane 66 extends axially aft from leading edge 74.
- Groove 76 is formed on an aft end of stationary half vane 66 and is thus axially aft of leading edge 74.
- Groove 76 extends on stationary half vane 66 from inner shroud 64 to ringcase 62.
- groove 76 has a concave cross-sectional profile such that groove 76 has a surface that curves axially forward into stationary half vane 66.
- Partial suction surface 78 of stationary half vane 66 extends radially from inner shroud 64 to ringcase 62 and extends axially from leading edge 74 to groove 76.
- Partial pressure surface 80 of stationary half vane 66 also extends radially from inner shroud 64 to ringcase 62 and extends axially from leading edge 74 to groove 76 opposite partial suction surface 78.
- Groove 76 is positioned between partial suction surface 78 and partial pressure surface 80 at the aft end of stationary half vane 66. As shown in FIG.
- an undercut 94 can be formed between the aft end of each stationary half vane 66 and inner shroud 64 to reduce bending stress concentrations between half vane 66 and inner shroud 64 during operation of gas turbine engine 20 (shown in FIG. 1 ).
- Another undercut (shown in FIGS. 8 and 9 ) can be formed between the aft end of each stationary half vane 66 and ringcase 62 to reduce bending stress concentrations between half vane 66 and ringcase 62 during operation of gas turbine engine 20.
- the plurality of outer trunnion holes 92 are formed in ringcase 62 aft of the plurality of stationary half vanes 66. Each of the outer trunnion holes 92 is circumferentially aligned with one of the plurality of stationary half vanes 66 and extends radially through ringcase 62 just aft of groove 76. A boss can be formed around each of the outer trunnion holes 92 to reinforce the circumference of the outer trunnion holes 92.
- the plurality of sockets 86 are formed on aft edge 84 of inner shroud 64. Each socket 86 of the plurality of sockets 86 is circumferentially aligned with one of the plurality of stationary half vanes 66.
- inner trunnion holes 98 are formed by inner shroud 64 and aft ring 96.
- Aft ring 96 abuts aft edge 84 of inner shroud 64 and is fastened to mounting tabs 72 of inner shroud 64.
- Half of each inner trunnion hole 98 is formed on aft edge 84 over one of the plurality of sockets 86, and the other half of each inner trunnion hole 98 is formed on aft ring 96.
- groove 76 on each of stationary half vanes 66, the plurality of outer trunnion holes 92, the plurality of sockets 86, and the inner trunnion holes 98 are features that accommodate the assembly of a plurality of variable half vanes 100 onto integral half vane structure 60.
- FIG. 5 is a cross-sectional view in the axial-radial plane of integral half vane structure 60 assembled with a plurality of rotating variable half vanes 100.
- FIG. 6 is a cross-sectional view of one of the stationary half vanes 66 and one of the variable half vanes 100.
- Each one of the variable half vanes 100 in FIGS. 5 and 6 include trailing edge 102, joining edge 104, first trunnion 106, second trunnion 108, button 110, partial pressure surface 120, and partial suction surface 122.
- Trunnion nuts 112 and outer surface 114 and ribs 116 of ringcase 62 are shown in the embodiment of FIG. 5 .
- Each variable half vane 100 is assembled onto integral half vane structure 60 immediately aft of one of stationary half vanes 66.
- trailing edge 102 extends radially between inner shroud 64 and ringcase 62.
- Joining edge 104 is forward of trailing edge 102 and aft of groove 76.
- Joining edge 104 extends radially from inner shroud 64 to ringcase 62.
- joining edge 104 of each variable half vane 100 is configured to mate with groove 76 on the adjacent stationary half vane 66.
- joining edge 104 is rounded with a convex cross-sectional profile, so as to correspond with the concave profile of groove 76.
- Partial suction surface 122 of variable half vane 100 extends from joining edge 104 to trailing edge 102.
- Partial pressure surface 120 of variable half vane 100 extends from joining edge 104 to trailing edge 102 opposite partial suction surface 122.
- Partial suction surface 122 and partial pressure surface 120 of variable half vane 100 cooperate with partial suction surface 78 and partial pressure surface 80 of stationary half vane 66 respectively to create a complete airfoil profile that extends axially from leading edge 74 to trailing edge 102.
- the portion of the airfoil profile formed by stationary half vane 66 does not move or change position during operation of gas turbine engine 20 (shown in FIG. 1 ), whereas the portion of the airfoil profile formed by variable half vane 100 is able to pivot and move on axis R relative stationary half vane 66.
- first trunnion 106 extends radially outward proximate joining edge 104 and into one of outer trunnion holes 92 on ringcase 62.
- Trunnion nut 112 is fastened to first trunnion 106 to fasten variable half vane 100 to ringcase 62.
- Second trunnion 108 extends radially inward proximate joining edge 104 and is positioned aft of aft edge 84 (shown in FIG. 3 ) of inner shroud 64. Second trunnion 108 extends through one of inner trunnion holes 98 (shown in FIG. 4 ).
- Button 110 is formed on second trunnion 108, and a portion of button 110 is received by one of the plurality of sockets 86 on inner shroud 64. The other portion of button 110 is housed within a pocket on aft ring 96. Button 110, socket 86, and the pocket on aft ring 96 work together to connect variable half vane 100 to inner shroud 64.
- Aft ring 96 forms an inner diameter flow surface aft and downstream of stationary half vanes 66. Aft ring 96 also forms the inner diameter flow surface under at least a portion of variable half vanes 100.
- ringcase 62 is axially longer than inner shroud 64 and extends aft of variable half vanes 100.
- ringcase 62 can be axially long enough such that aft end 90 of ringcase 62 can extend around a stage of rotor blades (not shown). Ringcase 62 can also increase in diameter from aft of stationary half vanes 66.
- ribs 116 are formed on outer surface 114 of ringcase 62 to stiffen ringcase 62 against bending and other forces integral half vane structure 60 may encounter during operation of gas turbine engine 20 (shown in FIG. 1 ).
- the configuration of ribs 116 is discussed below with reference to FIG. 7 .
- FIG. 7 is a perspective view of ribs 116 on outer surface 114 of ringcase 62.
- ribs 116 include axial ribs 116A, first angled ribs 116B, and second angled ribs 116C. Ribs 116 also include nodes 124.
- Axial ribs 116A, first angled ribs 116B, and second angled ribs 116C are all formed on outer surface 114 of ringcase 62 aft of stationary half vanes 66 (shown in FIGS. 2-6 ).
- Axial ribs 116A extend on outer surface 114 parallel to center axis CA and are circumferentially spaced apart from one another on outer surface 114.
- First angled ribs 116B extend on outer surface 114 non parallel to center axis CA and intersect axial ribs 116A at nodes 124.
- each of first angled ribs 116B intersect two axial ribs 116A.
- Second angled ribs 116C extend on outer surface 114 non parallel to center axis CA and intersect axial ribs 116A and first angled ribs 116B at nodes 124.
- each of second angled ribs 116C intersects two axial ribs 116A and two first angled ribs 116B.
- First angled ribs 116B can intersect second angled ribs 116C at a forty-five degree angle. As shown in FIG.
- nodes 124 are not centered on axial ribs 116A, but alternate such that nodes 124 are on a forward portion of every other axial rib 116A and on an aft portion of the remaining axial ribs 116A. Alternating the position of nodes 124 on axial ribs 116A distributes ribs 116 on outer surface 114 of ringcase 62 such that ribs 116 evenly reinforce ringcase 62.
- Axial ribs 116A, first angled ribs 116B, and second angled ribs 116C all increase in radial thickness in the axially aft direction to accommodate the increasing diameter of ringcase 62, as discussed above with reference to FIG. 5 .
- FIGS. 8-10 disclose another embodiment of integral half vane structure 60 with additional features that strengthen and alleviate stress in integral half vane structure 60.
- FIG. 8 is a perspective cross-sectional view of integral half vane structure 60 with circumferential rib 126 formed on ringcase 62, and first undercuts 94A and second undercuts 94B both formed on stationary half vanes 66.
- FIG. 9 is an enlarged view, taken from Circle A in FIG. 8 , of ringcase 62, outer trunnion holes 92, circumferential rib 126, stationary half vanes 66, and first undercuts 94A.
- FIG. 10 is an enlarged view, taken from Circle B in FIG. 8 , of inner shroud 64, stationary half vanes 66, and second undercuts 94B.
- circumferential rib 126 is formed on outer surface 114 of ringcase 62 and extends radially outward from ringcase 62. Circumferential rib 126 extends the full circumference of ringcase 62. Circumferential rib 126 is positioned on ringcase 62 axially forward of ribs 116 and axially aft of stationary half vanes 66 and outer trunnion holes 92. Circumferential rib 126 can be positioned over variable half vanes 100 (shown in FIG. 5 ) such that circumferential rib 126 extends around variable half vanes 100.
- Circumferential rib 126 stiffens ringcase 62 against case pressures that act on ringcase 62, reducing stress that is concentrated between the junction of stationary half vanes 66 and ringcase 62 during operation of gas turbine engine 20 (shown in FIG. 1 ).
- first undercut 94A is formed on an aft end of stationary half vane 66 between groove 76 and ringcase 62.
- second undercut 94B is formed on the aft end of each stationary half vane 66 between groove 76 and inner shroud 64.
- First undercuts 94A and second undercuts 94B reduce the amount of stress that is concentrated between both the junction of stationary half vanes 66 and ringcase 62 and the junction of stationary half vanes 66 and inner shroud 64.
- First undercuts 94A and second undercuts 94B sufficiently reduce the stress concentrations in stationary half canes 66 such that integral half vane structure 60 can be formed from lightweight materials, like titanium.
- the present disclosure provides numerous advantages and benefits.
- the present disclosure provides integral half vane structure 60 with ringcase 62, inner shroud 64, and a plurality of stationary half vanes 66.
- Stationary half vanes 66 are integral with ring case 62 and inner shroud 64. Because stationary half vanes 66 are integral with ring case 62 and inner shroud 64, the position of each stationary half vane 66 can be tightly controlled during manufacturing and does not shift or vary like prior art vane assemblies.
- stationary half vanes 66 integral with ringcase 62 and inner shroud 64, fewer parts, fasteners, and overall mass are required to assemble a vane stage that incorporates integral half vane structure 60 than prior art vane assemblies.
- the inclusion of circumferential rib 126 and ribs 116 stiffens ringcase 62 and allows ringcase 62 to be longer and encircle a downstream stage of rotor blades (not shown).
- First and second undercuts 94A, 94B on integral half vane structure 60 sufficiently reduce stress concentrations in integral half vane structure 60 during operation to allow integral half vane structure 60 to be made from titanium or other lightweight materials with similar properties.
- a vane stage in one embodiment, includes a ringcase extending circumferentially about a center axis of the vane stage.
- the ringcase extends completely about the center axis to form a first ring.
- An inner shroud extends circumferentially about the center axis of the vane stage.
- the inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis.
- a plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
- the vane stage of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
- a vane stage in another embodiment, includes a ringcase extending circumferentially about a center axis of the vane stage.
- the ringcase extends completely about the center axis to form a first non-segmented ring.
- An inner shroud extends circumferentially about the center axis of the vane stage.
- the inner shroud extends completely about the center axis to form a second non-segmented ring radially within the ringcase relative the center axis.
- a plurality of stationary half vanes extend radially between the ringcase and the inner shroud.
- the plurality of stationary half vanes are circumferentially spaced about the center axis and are integrally connected to the ringcase and the inner shroud.
- Each of the plurality of stationary half vanes includes both a leading edge extending radially from the inner shroud to the ringcase, and a groove extending radially from the inner shroud to the ringcase aft of the leading edge.
- a partial suction surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove.
- a partial pressure surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove opposite the partial suction surface.
- the groove is positioned between the partial suction surface and the partial pressure surface.
- the vane stage of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
- a vane stage in another embodiment, includes a ringcase extending circumferentially about a center axis of the vane stage.
- the ringcase extends completely about the center axis to form a first non-segmented ring.
- An inner shroud extends circumferentially about the center axis of the vane stage.
- the inner shroud extends completely about the center axis to form a second non-segmented ring positioned radially within the ringcase relative the center axis.
- a plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
- a plurality of trunnion holes are formed in the ringcase aft of the plurality of stationary half vanes. Each trunnion hole of the plurality of trunnion holes is circumferentially aligned with one of the plurality of stationary half vanes and extends radially through the ringcase.
- the vane stage of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
- any relative terms or terms of degree used herein such as “substantially”, “essentially”, “generally”, “approximately”, and the like, should be interpreted in accordance with and subject to any applicable definitions or limits expressly stated herein. In all instances, any relative terms or terms of degree used herein should be interpreted to broadly encompass any relevant disclosed embodiments as well as such ranges or variations as would be understood by a person of ordinary skill in the art in view of the entirety of the present disclosure, such as to encompass ordinary manufacturing tolerance variations, incidental alignment variations, transitory vibrations and sway movements, temporary alignment or shape variations induced by operational conditions, and the like.
- FIGS. 1-10 disclose integral half vane structure 60 being used in compressor section 24, integral half vane structure 60 can be adapted for use in turbine section 28. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The present disclosure relates to variable area vanes in gas turbine engines.
Gas turbine engines typically include a compressor section, a combustor section, and a turbine section. During operation, air is pressurized in the compressor section, and is mixed with fuel and burned in the combustor section to generate hot combustion gases. The hot combustion gases are communicated through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads. - Typically, both the compressor and turbine sections include alternating arrays of vanes and rotating blades that extend into a core airflow path of the gas turbine engine. For example, in the compressor section, compressor blades rotate to pull air into the compressor section for compression. The compressor vanes guide the airflow between different arrays (also called stages) of rotating blades and prepare the airflow for a downstream array of blades. Some compressor sections include variable area vanes, which include vanes that are moveable to vary the area or direction of the flow of the core airflow path between two stages of rotating blades. Movement of the variable area vanes is controlled to optimize the performance of the gas turbine engine during various operating conditions.
- In one aspect of the disclosure, a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
- In another aspect of the disclosure, a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first non-segmented ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second non-segmented ring radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud. The plurality of stationary half vanes are circumferentially spaced about the center axis and are integrally connected to the ringcase and the inner shroud. Each of the plurality of stationary half vanes includes both a leading edge extending radially from the inner shroud to the ringcase, and a groove extending radially from the inner shroud to the ringcase aft of the leading edge. A partial suction surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove. A partial pressure surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove opposite the partial suction surface. The groove is positioned between the partial suction surface and the partial pressure surface.
- In another aspect of the disclosure, a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first non-segmented ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second non-segmented ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud. A plurality of trunnion holes are formed in the ringcase aft of the plurality of stationary half vanes. Each trunnion hole of the plurality of trunnion holes is circumferentially aligned with one of the plurality of stationary half vanes and extends radially through the ringcase.
- Persons of ordinary skill in the art will recognize that other aspects and embodiments of the present disclosure are possible in view of the entirety of the present disclosure, including the accompanying figures.
-
-
FIG. 1 is a partial cross-sectional view of a gas turbine engine. -
FIG. 2 is a perspective view of an integral half vane structure with an outer ringcase, and inner shroud, and a plurality of stationary half vanes. -
FIG. 3 is a perspective cross-sectional view of the integral half vane structure fromFIG. 2 with the cross section taken in the axial-radial plane. -
FIG. 4 is a perspective cross-sectional view of the integral half vane structure ofFIGS. 2 and3 with the cross section taken in the axial-circumferential plane. -
FIG. 5 is a cross-sectional view in the axial-radial plane of the integral half vane structure assembled with a plurality of rotating variable half vanes. -
FIG. 6 is a cross-sectional view of one of the stationary half vanes and one of variable half vanes fromFIG. 5 . -
FIG. 7 is a perspective view of ribs on the outer surface of the ringcase of the integral half vane structure ofFIGS. 1 and5 . -
FIG. 8 is a perspective cross-sectional view of another embodiment of the integral half vane structure with an outer ringcase, and inner shroud, and a plurality of stationary half vanes, with the cross section taken in the axial-radial plane. -
FIG. 9 is an enlarged perspective cross-sectional view of the outer ringcase and the plurality of stationary half vanes taken from Circle A inFIG. 8 . -
FIG. 10 is an enlarged perspective cross-sectional view of the inner shroud and the plurality of stationary half vanes taken from Circle B inFIG. 8 . - While the above-identified drawing figures set forth one or more embodiments of the invention, other embodiments are also contemplated. In all cases, this disclosure presents the invention by way of representation and not limitation. It should be understood that numerous other modifications and embodiments can be devised by those skilled in the art, which fall within the scope and spirit of the principles of the invention. The figures may not be drawn to scale, and applications and embodiments of the present invention may include features and components not specifically shown in the drawings. Like reference numerals identify similar structural elements.
- The present disclosure provides a vane stage with an integral half vane structure with an outer ringcase, an inner shroud, and a plurality of stationary half vanes. Rotating variable half vanes are assembled onto the integral half vane structure aft of the stationary half vanes. Together, the stationary half vanes and the variable half vanes form an array of vanes where each vane has a fixed leading edge and an adjustable trailing edge that can be controlled to optimize the performance of a gas turbine engine during various operating conditions. Because the plurality of stationary half vanes, the outer ringcase and the inner shroud are integral, the position of stationary half vanes within integral half vane structure can be tightly controlled, which leads to tighter tolerances between the stationary half vanes and the variable half vanes. Tighter tolerances between the stationary half vanes and the variable vanes reduce flow irregularities across the vane stage. Making the ringcase, the inner shroud, and the plurality of stationary half vanes integral also reduces the number of parts and the weight of the vane stage when compared to traditional vane stages where vanes and shroud segments are fastened together into a vane pack.
-
FIG. 1 is a quarter-sectional view that schematically illustrates examplegas turbine engine 20 that includesfan section 22,compressor section 24,combustor section 26 andturbine section 28.Fan section 22 drives air along bypass flow path B in bypass duct D whilecompressor section 24 draws air in along core flow path C where air is compressed and communicated tocombustor section 26. Incombustor section 26, air is mixed with fuel and ignited to generate a high pressure exhaust gas stream that expands throughturbine section 28 where energy is extracted and utilized to drivefan section 22 andcompressor section 24. Although the disclosed non-limiting embodiment depicts a turbofan gas turbine engine, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. - The example
gas turbine engine 20 generally includeslow speed spool 30 andhigh speed spool 32 mounted for rotation about center axis CA ofgas turbine engine 20 relative to enginestatic structure 36 viaseveral bearing assemblies 38. It should be understood thatvarious bearing assemblies 38 at various locations may alternatively or additionally be provided. -
Low speed spool 30 generally includesinner shaft 40 that connectsfan 42 and low pressure (or first)compressor 44 to low pressure (or first)turbine 46.Inner shaft 40 drivesfan 42 through a speed change device, such as gearedarchitecture 48, to drivefan 42 at a lower speed thanlow speed spool 30. High-speed spool 32 includesouter shaft 50 that interconnects high pressure (or second)compressor 52 and high pressure (or second)turbine 54.Inner shaft 40 andouter shaft 50 are concentric and rotate via bearingassemblies 38 about center axis CA. -
Combustor 56 is arranged betweenhigh pressure compressor 52 andhigh pressure turbine 54.Mid-turbine frame 57 of enginestatic structure 36 can be arranged generally betweenhigh pressure turbine 54 andlow pressure turbine 46.Mid-turbine frame 57 furthersupports bearing assemblies 38 inturbine section 28 as well as setting airflow entering thelow pressure turbine 46.Mid-turbine frame 57 includesairfoils 59 which are in core flow path C. The air in core flow path C is compressed first bylow pressure compressor 44 and then byhigh pressure compressor 52. Next, the air is mixed with fuel and ignited incombustor 56 to produce high speed exhaust gases that are then expanded throughhigh pressure turbine 54, mid-turbine frame 58, andlow pressure turbine 46. As discussed below with reference toFIGS. 2-4 ,compressor section 24 can include an integralhalf vane structure 60 that is used in a variable vane stage. -
FIGS. 2-4 will be discussed concurrently.FIG. 2 is a perspective view of integralhalf vane structure 60.FIG. 3 is a perspective cross-sectional view of integralhalf vane structure 60 with the cross section taken in the axial-radial plane.FIG. 4 is a perspective cross-sectional view of integralhalf vane structure 60 with the cross section taken in the axial-circumferential plane. As shown inFIGS. 2-4 , integralhalf vane structure 60 includesringcase 62,inner shroud 64, and a plurality of stationary half vanes 66. As shown best inFIG. 2 , integralhalf vane structure 60 also includesforward flange 68 andaft flange 70 onring case 62, and mountingtabs 72 oninner shroud 64. As shown best inFIGS. 3 and4 , eachstationary half vane 66 in the plurality ofhalf vanes 66 includes leadingedge 74,groove 76,partial suction surface 78, andpartial pressure surface 80. Inner shroud includes forward edge 82, aftedge 84, and a plurality ofsockets 86.Ringcase 62 includes forward edge 88, aft edge 90 (shown inFIG. 2 ), and a plurality of outer trunnion holes 92. As shown best inFIG. 4 , eachstationary half vane 66 can also include undercut 94.Aft ring 96 and inner trunnion holes 98 are also shown inFIG. 4 . -
Ringcase 62 extends circumferentially about center axis CA.Ringcase 62 extends completely about center axis CA to form a first complete and non-segmented ring.Ringcase 62 extends axially fromforward edge 88 toaft edge 90.Forward flange 68 is formed onforward edge 88 ofringcase 62 and extends radially outward fromringcase 62.Aft flange 70 is formed onaft edge 90 ofringcase 62 and extends radially outward fromringcase 62.Forward flange 68 andaft flange 70 are configured to allowringcase 62 to be mounted between two axially-adjacent structures (not shown) ingas turbine engine 20.Inner shroud 64 also extends circumferentially about center axis CA. Similar to ringcase 62,inner shroud 64 extends completely about center axis CA to form a second complete and non-segmented ring.Inner shroud 64 is smaller in diameter thanringcase 62 and is positioned radially withinringcase 62 such thatringcase 62 andinner shroud 64 are concentric on central axis CA.Inner shroud 64 extends axially fromforward edge 82 toaft edge 84. Mountingtabs 72 are formed on a radially inner surface ofinner shroud 64 betweenforward edge 82 andaft edge 84. Mountingtabs 72 are circumferentially spaced from one another and extend radially inward frominner shroud 64. Mountingtabs 72 are provided to connectinner shroud 64 to forward and aft adjacent structures (such asaft ring 96 shown inFIG. 5 ) ingas turbine engine 20. - The plurality of
stationary half vanes 66 extend radially betweenringcase 62 andinner shroud 64 and connect ringcase 62 andinner shroud 64 together.Stationary half vanes 66 are spaced circumferentially about center axis CA.Stationary half vanes 66 are integral withring case 62 andinner shroud 64. Integralhalf vane structure 60 can be formed by machiningringcase 62,inner shroud 64 andstationary half vanes 66 from a single piece of metal. Integralhalf vane structure 60 can also be made by first formingringcase 62, welding a cylindrical plate (not shown) insideringcase 62, and machining the cylindrical plate to forminner shroud 64 and stationary half vanes 66. Integralhalf vane structure 60 can also be made by separately formingringcase 62,inner shroud 64, andstationary half vanes 66, and weldingringcase 62,inner shroud 64, andstationary half vanes 66 together. Integralhalf vane structure 60 can also be formed through additive manufacturing. - As shown best in
FIGS. 3 and4 , leadingedge 74 of eachstationary half vane 66 extends radially frominner shroud 64 toringcase 62. The body ofstationary half vane 66 extends axially aft from leadingedge 74.Groove 76 is formed on an aft end ofstationary half vane 66 and is thus axially aft of leadingedge 74.Groove 76 extends onstationary half vane 66 frominner shroud 64 toringcase 62. In the embodiments ofFIGS. 3 and4 , groove 76 has a concave cross-sectional profile such thatgroove 76 has a surface that curves axially forward intostationary half vane 66.Partial suction surface 78 ofstationary half vane 66 extends radially frominner shroud 64 to ringcase 62 and extends axially from leadingedge 74 to groove 76.Partial pressure surface 80 ofstationary half vane 66 also extends radially frominner shroud 64 to ringcase 62 and extends axially from leadingedge 74 to groove 76 oppositepartial suction surface 78.Groove 76 is positioned betweenpartial suction surface 78 andpartial pressure surface 80 at the aft end ofstationary half vane 66. As shown inFIG. 4 , an undercut 94 can be formed between the aft end of eachstationary half vane 66 andinner shroud 64 to reduce bending stress concentrations betweenhalf vane 66 andinner shroud 64 during operation of gas turbine engine 20 (shown inFIG. 1 ). Another undercut (shown inFIGS. 8 and9 ) can be formed between the aft end of eachstationary half vane 66 and ringcase 62 to reduce bending stress concentrations betweenhalf vane 66 andringcase 62 during operation ofgas turbine engine 20. - The plurality of outer trunnion holes 92 are formed in
ringcase 62 aft of the plurality of stationary half vanes 66. Each of the outer trunnion holes 92 is circumferentially aligned with one of the plurality ofstationary half vanes 66 and extends radially throughringcase 62 just aft ofgroove 76. A boss can be formed around each of the outer trunnion holes 92 to reinforce the circumference of the outer trunnion holes 92. The plurality ofsockets 86 are formed onaft edge 84 ofinner shroud 64. Eachsocket 86 of the plurality ofsockets 86 is circumferentially aligned with one of the plurality of stationary half vanes 66. As shown best inFIG. 4 , inner trunnion holes 98 are formed byinner shroud 64 andaft ring 96.Aft ring 96 abutsaft edge 84 ofinner shroud 64 and is fastened to mountingtabs 72 ofinner shroud 64. Half of eachinner trunnion hole 98 is formed onaft edge 84 over one of the plurality ofsockets 86, and the other half of eachinner trunnion hole 98 is formed onaft ring 96. As discussed below with reference toFIGS. 5 and6 , groove 76 on each ofstationary half vanes 66, the plurality of outer trunnion holes 92, the plurality ofsockets 86, and the inner trunnion holes 98 are features that accommodate the assembly of a plurality ofvariable half vanes 100 onto integralhalf vane structure 60. -
FIGS. 5 and6 will be discussed concurrently.FIG. 5 is a cross-sectional view in the axial-radial plane of integralhalf vane structure 60 assembled with a plurality of rotating variable half vanes 100.FIG. 6 is a cross-sectional view of one of thestationary half vanes 66 and one of the variable half vanes 100. Each one of thevariable half vanes 100 inFIGS. 5 and6 include trailingedge 102, joiningedge 104,first trunnion 106,second trunnion 108,button 110,partial pressure surface 120, andpartial suction surface 122.Trunnion nuts 112 andouter surface 114 andribs 116 ofringcase 62 are shown in the embodiment ofFIG. 5 . - Each
variable half vane 100 is assembled onto integralhalf vane structure 60 immediately aft of one of stationary half vanes 66. On each ofvariable half vanes 100, trailingedge 102 extends radially betweeninner shroud 64 andringcase 62. Joiningedge 104 is forward of trailingedge 102 and aft ofgroove 76. Joiningedge 104 extends radially frominner shroud 64 toringcase 62. As shown best inFIG. 6 , joiningedge 104 of eachvariable half vane 100 is configured to mate withgroove 76 on the adjacentstationary half vane 66. In the embodiment ofFIG. 6 , joiningedge 104 is rounded with a convex cross-sectional profile, so as to correspond with the concave profile ofgroove 76.Partial suction surface 122 ofvariable half vane 100 extends from joiningedge 104 to trailingedge 102.Partial pressure surface 120 ofvariable half vane 100 extends from joiningedge 104 to trailingedge 102 oppositepartial suction surface 122.Partial suction surface 122 andpartial pressure surface 120 ofvariable half vane 100 cooperate withpartial suction surface 78 andpartial pressure surface 80 ofstationary half vane 66 respectively to create a complete airfoil profile that extends axially from leadingedge 74 to trailingedge 102. The portion of the airfoil profile formed bystationary half vane 66 does not move or change position during operation of gas turbine engine 20 (shown inFIG. 1 ), whereas the portion of the airfoil profile formed byvariable half vane 100 is able to pivot and move on axis R relativestationary half vane 66. - On each of
variable half vanes 100,first trunnion 106 extends radially outward proximate joiningedge 104 and into one of outer trunnion holes 92 onringcase 62.Trunnion nut 112 is fastened tofirst trunnion 106 to fastenvariable half vane 100 toringcase 62.Second trunnion 108 extends radially inward proximate joiningedge 104 and is positioned aft of aft edge 84 (shown inFIG. 3 ) ofinner shroud 64.Second trunnion 108 extends through one of inner trunnion holes 98 (shown inFIG. 4 ).Button 110 is formed onsecond trunnion 108, and a portion ofbutton 110 is received by one of the plurality ofsockets 86 oninner shroud 64. The other portion ofbutton 110 is housed within a pocket onaft ring 96.Button 110,socket 86, and the pocket onaft ring 96 work together to connectvariable half vane 100 toinner shroud 64. -
Aft ring 96 forms an inner diameter flow surface aft and downstream of stationary half vanes 66.Aft ring 96 also forms the inner diameter flow surface under at least a portion of variable half vanes 100. As shown inFIG. 5 ,ringcase 62 is axially longer thaninner shroud 64 and extends aft of variable half vanes 100. In the embodiment ofFIG. 5 , ringcase 62 can be axially long enough such thataft end 90 ofringcase 62 can extend around a stage of rotor blades (not shown).Ringcase 62 can also increase in diameter from aft of stationary half vanes 66. Due to the longer axial length ofringcase 62,ribs 116 are formed onouter surface 114 ofringcase 62 to stiffenringcase 62 against bending and other forces integralhalf vane structure 60 may encounter during operation of gas turbine engine 20 (shown inFIG. 1 ). The configuration ofribs 116 is discussed below with reference toFIG. 7 . -
FIG. 7 is a perspective view ofribs 116 onouter surface 114 ofringcase 62. As shown inFIG. 7 ,ribs 116 includeaxial ribs 116A, firstangled ribs 116B, and secondangled ribs 116C.Ribs 116 also includenodes 124.Axial ribs 116A, firstangled ribs 116B, and secondangled ribs 116C are all formed onouter surface 114 ofringcase 62 aft of stationary half vanes 66 (shown inFIGS. 2-6 ).Axial ribs 116A extend onouter surface 114 parallel to center axis CA and are circumferentially spaced apart from one another onouter surface 114. Firstangled ribs 116B extend onouter surface 114 non parallel to center axis CA and intersectaxial ribs 116A atnodes 124. - In the embodiment of
FIG. 7 , each of firstangled ribs 116B intersect twoaxial ribs 116A. Secondangled ribs 116C extend onouter surface 114 non parallel to center axis CA and intersectaxial ribs 116A and firstangled ribs 116B atnodes 124. In the embodiment ofFIG. 7 , each of secondangled ribs 116C intersects twoaxial ribs 116A and two firstangled ribs 116B. Firstangled ribs 116B can intersect secondangled ribs 116C at a forty-five degree angle. As shown inFIG. 7 ,nodes 124 are not centered onaxial ribs 116A, but alternate such thatnodes 124 are on a forward portion of every otheraxial rib 116A and on an aft portion of the remainingaxial ribs 116A. Alternating the position ofnodes 124 onaxial ribs 116A distributesribs 116 onouter surface 114 ofringcase 62 such thatribs 116 evenly reinforceringcase 62.Axial ribs 116A, firstangled ribs 116B, and secondangled ribs 116C all increase in radial thickness in the axially aft direction to accommodate the increasing diameter ofringcase 62, as discussed above with reference toFIG. 5 . -
FIGS. 8-10 will be discussed concurrently.FIGS. 8-10 disclose another embodiment of integralhalf vane structure 60 with additional features that strengthen and alleviate stress in integralhalf vane structure 60.FIG. 8 is a perspective cross-sectional view of integralhalf vane structure 60 withcircumferential rib 126 formed onringcase 62, andfirst undercuts 94A andsecond undercuts 94B both formed on stationary half vanes 66.FIG. 9 is an enlarged view, taken from Circle A inFIG. 8 , ofringcase 62, outer trunnion holes 92,circumferential rib 126,stationary half vanes 66, andfirst undercuts 94A.FIG. 10 is an enlarged view, taken from Circle B inFIG. 8 , ofinner shroud 64,stationary half vanes 66, andsecond undercuts 94B. - As shown in
FIGS. 8 and9 ,circumferential rib 126 is formed onouter surface 114 ofringcase 62 and extends radially outward fromringcase 62.Circumferential rib 126 extends the full circumference ofringcase 62.Circumferential rib 126 is positioned onringcase 62 axially forward ofribs 116 and axially aft ofstationary half vanes 66 and outer trunnion holes 92.Circumferential rib 126 can be positioned over variable half vanes 100 (shown inFIG. 5 ) such thatcircumferential rib 126 extends around variable half vanes 100.Circumferential rib 126 stiffens ringcase 62 against case pressures that act onringcase 62, reducing stress that is concentrated between the junction ofstationary half vanes 66 andringcase 62 during operation of gas turbine engine 20 (shown inFIG. 1 ). - On each
stationary half vane 66, first undercut 94A is formed on an aft end ofstationary half vane 66 betweengroove 76 andringcase 62. As shown inFIGS. 8 and10 , second undercut 94B is formed on the aft end of eachstationary half vane 66 betweengroove 76 andinner shroud 64. During operation ofgas turbine engine 20, pressure insideringcase 62 imparts stress ontoringcase 62. Becausestationary half vanes 66 are integral withringcase 62, stress is transferred fromringcase 62 tostationary half vanes 66 andinner shroud 64. First undercuts 94A andsecond undercuts 94B reduce the amount of stress that is concentrated between both the junction ofstationary half vanes 66 andringcase 62 and the junction ofstationary half vanes 66 andinner shroud 64. First undercuts 94A andsecond undercuts 94B sufficiently reduce the stress concentrations instationary half canes 66 such that integralhalf vane structure 60 can be formed from lightweight materials, like titanium. - In view of the foregoing description, it will be recognized that the present disclosure provides numerous advantages and benefits. For example, the present disclosure provides integral
half vane structure 60 withringcase 62,inner shroud 64, and a plurality of stationary half vanes 66.Stationary half vanes 66 are integral withring case 62 andinner shroud 64. Becausestationary half vanes 66 are integral withring case 62 andinner shroud 64, the position of eachstationary half vane 66 can be tightly controlled during manufacturing and does not shift or vary like prior art vane assemblies. Furthermore, by makingstationary half vanes 66 integral withringcase 62 andinner shroud 64, fewer parts, fasteners, and overall mass are required to assemble a vane stage that incorporates integralhalf vane structure 60 than prior art vane assemblies. The inclusion ofcircumferential rib 126 andribs 116 stiffens ringcase 62 and allows ringcase 62 to be longer and encircle a downstream stage of rotor blades (not shown). First andsecond undercuts half vane structure 60 sufficiently reduce stress concentrations in integralhalf vane structure 60 during operation to allow integralhalf vane structure 60 to be made from titanium or other lightweight materials with similar properties. - The following are non-exclusive descriptions of possible embodiments of the present invention.
- In one embodiment, a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
- The vane stage of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
- each of the plurality of stationary half vanes further comprises: a first undercut formed between the ringcase and the aft end of the stationary half vane; and a second undercut formed between the inner shroud and an aft end of the stationary half vane;
- the ringcase further comprise: a circumferential rib extending radially outward from the ringcase aft of the plurality of stationary half vanes and forward of an aft end of the ringcase, wherein the circumferential rib extends circumferentially around the ringcase;
- each of the plurality of stationary half vanes comprises: a leading edge extending radially from the inner shroud to the ringcase; a concave groove extending radially from the inner shroud to the ringcase and aft of the leading edge; a partial suction surface extending radially from the inner shroud to the ringcase and extending axially from the leading edge to the concave groove; and a partial pressure surface extending radially from the inner shroud to the ringcase and extending axially from the leading edge to the concave groove opposite the partial suction surface, and wherein the concave groove is positioned between the partial suction surface and the partial pressure surface;
- a plurality of trunnion holes formed in the ringcase, wherein each trunnion hole of the plurality of trunnion holes is circumferentially aligned with one of the plurality of stationary half vanes and extends radially through the ringcase aft of the concave groove, and wherein the circumferential rib is aft of the plurality of trunnion holes;
- a plurality of variable half vanes, wherein each of the plurality of variable half vanes comprises: a trailing edge extending radially between the inner shroud and the ringcase; a convex edge extending radially from the inner shroud to the ringcase, wherein the convex edge is forward of the trailing edge and configured to mate with the concave groove of one of the plurality of stationary half vanes; a first trunnion extending radially from the convex edge into one of the plurality of trunnion holes; and a second trunnion extending radially from the convex edge opposite the first trunnion, wherein the second trunnion is aft of the aft edge of the inner shroud;
- the ringcase is axially longer than the inner shroud and increases in diameter aft of the plurality of stationary half vanes;
- the ringcase comprises a plurality of ribs formed on an outer surface of the ringcase aft of the circumferential rib, wherein each of the plurality of ribs increases in radial thickness in an aft direction; and/or
- the plurality of ribs comprises: an axial rib extending parallel to the center axis; a first angled rib intersecting the axial rib at a node; and a second angled rib intersecting the axial rib and the first angled rib at the node.
- In another embodiment, a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first non-segmented ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second non-segmented ring radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud. The plurality of stationary half vanes are circumferentially spaced about the center axis and are integrally connected to the ringcase and the inner shroud. Each of the plurality of stationary half vanes includes both a leading edge extending radially from the inner shroud to the ringcase, and a groove extending radially from the inner shroud to the ringcase aft of the leading edge. A partial suction surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove. A partial pressure surface extends radially from the inner shroud to the ringcase and extends axially from the leading edge to the groove opposite the partial suction surface. The groove is positioned between the partial suction surface and the partial pressure surface.
- The vane stage of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
- each of the plurality of stationary half vanes further comprises: a first undercut formed between the groove and the ringcase and a second undercut formed between the groove and the inner shroud;
- the ringcase is axially longer than the inner shroud and the ringcase further comprises: a rib extending radially outward from the ringcase aft of the plurality of stationary half vanes and forward of an aft end of the ringcase, wherein the rib extends circumferentially around the ringcase;
- a plurality of trunnion holes formed in the ringcase, wherein each trunnion hole of the plurality of trunnion holes is circumferentially aligned with one of the plurality of stationary half vanes and extends radially through the ringcase aft of the groove; and/or
- a plurality of variable half vanes, wherein each of the plurality of variable half vanes comprises: a trailing edge extending radially between the inner shroud and the ringcase; a joining edge extending radially from the inner shroud to the ringcase, wherein the joining edge is forward of the trailing edge and configured to mate with the groove of one of the plurality of stationary half vanes; a first trunnion extending radially from the joining edge into one of the plurality of trunnion holes; and a second trunnion extending radially from the joining edge opposite the first trunnion, wherein the second trunnion is aft of the aft edge of the inner shroud.
- In another embodiment, a vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first non-segmented ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second non-segmented ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud. A plurality of trunnion holes are formed in the ringcase aft of the plurality of stationary half vanes. Each trunnion hole of the plurality of trunnion holes is circumferentially aligned with one of the plurality of stationary half vanes and extends radially through the ringcase.
- The vane stage of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
- the ringcase further comprises: a rib extending radially outward from the ringcase aft of the plurality of trunnion holes and forward of an aft end of the ringcase, wherein the rib extends circumferentially around the ringcase;
- each of the plurality of stationary half vanes comprises: a leading edge extending radially from the inner shroud to the ringcase; a groove extending radially from the inner shroud to the ringcase and aft of the leading edge, wherein the groove has a concave cross-sectional profile; a partial suction surface extending radially from the inner shroud to the ringcase and extending axially from the leading edge to the groove; and a partial pressure surface extending radially from the inner shroud to the ringcase and extending axially from the leading edge to the groove opposite the partial suction surface, and wherein the groove is positioned between the partial suction surface and the partial pressure surface;
- each of the plurality of stationary half vanes further comprises: a first undercut formed between the groove and the ringcase; and a second undercut formed between the groove and the inner shroud;
- a plurality of variable half vanes, wherein each of the plurality of variable half vanes comprises: a trailing edge extending radially between the inner shroud and the ringcase; a joining edge extending radially from the inner shroud to the ringcase, wherein the joining edge is forward of the trailing edge and configured to mate with the groove of one of the plurality of stationary half vanes; a first trunnion extending radially from the joining edge into one of the plurality of trunnion holes; and a second trunnion extending radially from the convex edge opposite the first trunnion, wherein the second trunnion is aft of an aft edge of the inner shroud; and/or
- the rib extends circumferentially around the plurality of variable half vanes.
- Any relative terms or terms of degree used herein, such as "substantially", "essentially", "generally", "approximately", and the like, should be interpreted in accordance with and subject to any applicable definitions or limits expressly stated herein. In all instances, any relative terms or terms of degree used herein should be interpreted to broadly encompass any relevant disclosed embodiments as well as such ranges or variations as would be understood by a person of ordinary skill in the art in view of the entirety of the present disclosure, such as to encompass ordinary manufacturing tolerance variations, incidental alignment variations, transitory vibrations and sway movements, temporary alignment or shape variations induced by operational conditions, and the like.
- While the invention has been described with reference to an exemplary embodiment(s), it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. For example, while
FIGS. 1-10 disclose integralhalf vane structure 60 being used incompressor section 24, integralhalf vane structure 60 can be adapted for use inturbine section 28. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (15)
- A vane stage comprising:a ringcase (62) extending circumferentially about a center axis (CA) of the vane stage, wherein the ringcase (62) extends completely about the center axis (CA) to form a first ring;an inner shroud (64) extending circumferentially about the center axis (CA) of the vane stage, wherein the inner shroud (64) extends completely about the center axis (CA) to form a second ring positioned radially within the ringcase (62) relative the center axis (CA); anda plurality of stationary half vanes (66) extending radially between the ringcase (62) and the inner shroud (64), wherein the plurality of stationary half vanes (66) are circumferentially spaced about the center axis (CA), andwherein the plurality of stationary half vanes (66) are integral with the ringcase (62) and the inner shroud (64).
- The vane stage of claim 1, wherein each of the plurality of stationary half vanes (66) further comprises:a first undercut (94A) formed between the ringcase (62) and an aft end of the stationary half vane (66); anda second undercut (94, 94B) formed between the inner shroud (64) and the aft end of the stationary half vane (66).
- The vane stage of any preceding claim, wherein the ringcase (62) further comprises:
a circumferential rib (126) extending radially outward from the ringcase (62) aft of the plurality of stationary half vanes (66) and forward of an aft end of the ringcase (62), wherein the circumferential rib (126) extends circumferentially around the ringcase (62). - The vane stage of claim 3, wherein each of the plurality of stationary half vanes (66) comprises:a leading edge (74) extending radially from the inner shroud (64) to the ringcase (62);a concave groove (76) extending radially from the inner shroud (64) to the ringcase (62) and aft of the leading edge (74);a partial suction surface (78) extending radially from the inner shroud (64) to the ringcase (62) and extending axially from the leading edge (74) to the concave groove (76); anda partial pressure surface (80) extending radially from the inner shroud (64) to the ringcase (62) and extending axially from the leading edge (74) to the concave groove (76) opposite the partial suction surface (78), andwherein the concave groove (76) is positioned between the partial suction surface (78) and the partial pressure surface (80).
- The vane stage of claim 4 further comprising:
a plurality of trunnion holes (92) formed in the ringcase (62), wherein each trunnion hole (92) of the plurality of trunnion holes (92) is circumferentially aligned with one of the plurality of stationary half vanes (66) and extends radially through the ringcase (62) aft of the concave groove (76), and wherein the circumferential rib (126) is aft of the plurality of trunnion holes (92). - The vane stage of claim 5 further comprising:
a plurality of variable half vanes (100), wherein each of the plurality of variable half vanes (100) comprises:a trailing edge (102) extending radially between the inner shroud (64) and the ringcase (62);a convex edge (104) extending radially from the inner shroud (64) to the ringcase (62), wherein the convex edge (104) is forward of the trailing edge (102) and configured to mate with the concave groove (76) of one of the plurality of stationary half vanes (66);a first trunnion (106) extending radially from the convex edge (104) into one of the plurality of trunnion holes (92); anda second trunnion (108) extending radially from the convex edge (104) opposite the first trunnion (106), wherein the second trunnion (108) is aft of the aft edge of the inner shroud (64). - The vane stage of any of claims 3 to 6, wherein the ringcase (62) comprises a plurality of ribs (116) formed on an outer surface of the ringcase (62) aft of the circumferential rib (126), wherein each of the plurality of ribs (116) increases in radial thickness in an aft direction.
- The vane stage of claim 7, wherein the plurality of ribs (116) comprises:an axial rib (116A) extending parallel to the center axis (CA);a first angled rib (116B) intersecting the axial rib (116A) at a node (124); anda second angled rib (116C) intersecting the axial rib (116A) and the first angled rib (116B) at the node (124).
- The vane stage of any preceding claim, wherein the ringcase (62) is axially longer than the inner shroud (64) and increases in diameter aft of the plurality of stationary half vanes (66).
- The vane stage of claim 1, further comprising:a plurality of trunnion holes (92) formed in the ringcase (62) aft of the plurality of stationary half vanes (66), wherein each trunnion hole (92) of the plurality of trunnion holes (92) is circumferentially aligned with one of the plurality of stationary half vanes (66) and extends radially through the ringcase (62);wherein the ringcase (62) forms a first non-segmented ring and the inner shroud (64) forms a second non-segmented ring.
- The vane stage of claim 10, wherein the ringcase (62) further comprises:
a rib (126) extending radially outward from the ringcase (62) aft of the plurality of trunnion holes (92) and forward of an aft end of the ringcase (62), wherein the rib (126) extends circumferentially around the ringcase (62). - The vane stage of claim 10 or 11, wherein each of the plurality of stationary half vanes (66) comprises:a leading edge (74) extending radially from the inner shroud (64) to the ringcase (62);a groove (76) extending radially from the inner shroud (64) to the ringcase (62) and aft of the leading edge (74), wherein the groove (76) has a concave cross-sectional profile;a partial suction surface (78) extending radially from the inner shroud (64) to the ringcase (62) and extending axially from the leading edge (74) to the groove (76); anda partial pressure surface (80) extending radially from the inner shroud (64) to the ringcase (62) and extending axially from the leading edge (74) to the groove (76) opposite the partial suction surface (78), andwherein the groove (76) is positioned between the partial suction surface (78) and the partial pressure surface (80).
- The vane stage of claim 12, wherein each of the plurality of stationary half vanes (66) further comprises:a first undercut (94A) formed between the groove (76) and the ringcase (62); anda second undercut (94, 94B) formed between the groove (76) and the inner shroud (64).
- The vane stage of claim 12 or 13 further comprising:
a plurality of variable half vanes (100), wherein each of the plurality of variable half vanes (100) comprises:a trailing edge (102) extending radially between the inner shroud (64) and the ringcase (62);a joining edge (104) extending radially from the inner shroud (64) to the ringcase (62), wherein the joining edge (104) is forward of the trailing edge (102) and configured to mate with the groove (76) of one of the plurality of stationary half vanes (66);a first trunnion (106) extending radially from the joining edge (104) into one of the plurality of trunnion holes (92); anda second trunnion (108) extending radially from the convex edge (104) opposite the first trunnion (106), wherein the second trunnion (108) is aft of an aft edge of the inner shroud (64). - The vane stage of claim 14, wherein a/the rib (126) extends circumferentially around the plurality of variable half vanes (100).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/184,632 US10794200B2 (en) | 2018-09-14 | 2018-11-08 | Integral half vane, ringcase, and id shroud |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3650637A1 true EP3650637A1 (en) | 2020-05-13 |
EP3650637B1 EP3650637B1 (en) | 2021-10-27 |
Family
ID=67875368
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19195967.5A Active EP3650637B1 (en) | 2018-11-08 | 2019-09-06 | Gas turbine vane stage with half vanes integral with an outer case and an inner shroud |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP3650637B1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20210284333A1 (en) * | 2020-03-16 | 2021-09-16 | Anthony Windisch | Small light vertical take-off and landing capable delta wing aircraft |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3990810A (en) * | 1975-12-23 | 1976-11-09 | Westinghouse Electric Corporation | Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine |
EP1340894A2 (en) * | 2002-02-28 | 2003-09-03 | General Electric Company | Variable inlet guide vanes for varying gas turbine engine inlet air flow |
US20050109011A1 (en) * | 2003-07-17 | 2005-05-26 | Snecma Moteurs | De-icing device for turbojet inlet guide wheel vane, vane provided with such a de-icing device, and aircraft engine equipped with such vanes |
-
2019
- 2019-09-06 EP EP19195967.5A patent/EP3650637B1/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3990810A (en) * | 1975-12-23 | 1976-11-09 | Westinghouse Electric Corporation | Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine |
EP1340894A2 (en) * | 2002-02-28 | 2003-09-03 | General Electric Company | Variable inlet guide vanes for varying gas turbine engine inlet air flow |
US20050109011A1 (en) * | 2003-07-17 | 2005-05-26 | Snecma Moteurs | De-icing device for turbojet inlet guide wheel vane, vane provided with such a de-icing device, and aircraft engine equipped with such vanes |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20210284333A1 (en) * | 2020-03-16 | 2021-09-16 | Anthony Windisch | Small light vertical take-off and landing capable delta wing aircraft |
US11661183B2 (en) * | 2020-03-16 | 2023-05-30 | D. Anthony Windisch | Small light vertical take-off and landing capable delta wing aircraft |
Also Published As
Publication number | Publication date |
---|---|
EP3650637B1 (en) | 2021-10-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US9915154B2 (en) | Ceramic matrix composite airfoil structures for a gas turbine engine | |
US8221071B2 (en) | Integrated guide vane assembly | |
EP3354858B1 (en) | Gas turbine seal | |
US20200024954A1 (en) | Integrated strut and igv configuration | |
EP2096029A2 (en) | Nose cone assembly and gas turbine engine comprising such an assemby | |
US20170114796A1 (en) | Compressor incorporating splitters | |
US11371380B2 (en) | Variable guide vane assembly and vane arms therefor | |
CA2942667C (en) | Gas turbine gearbox input shaft | |
EP3040511A1 (en) | Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades | |
US20170306768A1 (en) | Turbine engine shroud assembly | |
EP2984290B1 (en) | Integrally bladed rotor | |
US10968748B2 (en) | Non-axisymmetric end wall contouring with aft mid-passage peak | |
EP2589759A2 (en) | Mid-Turbine Bearing Support | |
EP2855898B1 (en) | Stator vane bumper ring | |
US10876411B2 (en) | Non-axisymmetric end wall contouring with forward mid-passage peak | |
EP3246517B1 (en) | Fastener openings for stress distribution | |
EP3650637B1 (en) | Gas turbine vane stage with half vanes integral with an outer case and an inner shroud | |
US10794200B2 (en) | Integral half vane, ringcase, and id shroud | |
US10781707B2 (en) | Integral half vane, ringcase, and id shroud | |
US10746041B2 (en) | Shroud and shroud assembly process for variable vane assemblies | |
US20190390688A1 (en) | Gas turbine engine airfoil | |
EP3333365B1 (en) | Stator with support structure feature for tuned airfoil | |
GB2415017A (en) | Heat shield for attachment to a casing of a gas turbine engine |
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 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
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 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20201112 |
|
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 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R079 Ref document number: 602019008647 Country of ref document: DE Free format text: PREVIOUS MAIN CLASS: F01D0005140000 Ipc: F04D0029020000 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F04D 29/02 20060101AFI20210218BHEP Ipc: F04D 29/56 20060101ALI20210218BHEP Ipc: F01D 9/04 20060101ALI20210218BHEP Ipc: F01D 5/14 20060101ALI20210218BHEP Ipc: F01D 17/14 20060101ALI20210218BHEP Ipc: F01D 17/16 20060101ALI20210218BHEP Ipc: F01D 25/24 20060101ALI20210218BHEP Ipc: F04D 29/54 20060101ALI20210218BHEP |
|
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: 20210419 |
|
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: 1442039 Country of ref document: AT Kind code of ref document: T Effective date: 20211115 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602019008647 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20211027 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1442039 Country of ref document: AT Kind code of ref document: T Effective date: 20211027 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20211027 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: 20211027 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: 20211027 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: 20220127 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: 20211027 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20220227 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: 20211027 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: 20220228 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: 20211027 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: 20220127 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: 20211027 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: 20211027 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: 20211027 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: 20220128 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: 20211027 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602019008647 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20211027 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: 20211027 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: 20211027 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: 20211027 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: 20211027 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: 20211027 |
|
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 |
|
26N | No opposition filed |
Effective date: 20220728 |
|
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: 20211027 |
|
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: 20211027 |
|
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: 20211027 |
|
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: 20220930 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20211027 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230521 |
|
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: 20220906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220930 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220906 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220930 |
|
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: 20220930 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230823 Year of fee payment: 5 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230822 Year of fee payment: 5 Ref country code: DE Payment date: 20230822 Year of fee payment: 5 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20211027 |
|
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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20211027 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: 20190906 |