EP3423680A1 - Air cooled turbine stator vanes - Google Patents

Air cooled turbine stator vanes

Info

Publication number
EP3423680A1
EP3423680A1 EP16710066.8A EP16710066A EP3423680A1 EP 3423680 A1 EP3423680 A1 EP 3423680A1 EP 16710066 A EP16710066 A EP 16710066A EP 3423680 A1 EP3423680 A1 EP 3423680A1
Authority
EP
European Patent Office
Prior art keywords
seal
cavity
insert
airfoil
impingement cooling
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16710066.8A
Other languages
German (de)
French (fr)
Inventor
Robert L. Memmen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Florida Turbine Technologies Inc
Original Assignee
Florida Turbine Technologies Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Florida Turbine Technologies Inc filed Critical Florida Turbine Technologies Inc
Publication of EP3423680A1 publication Critical patent/EP3423680A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the present invention relates generally to a gas turbine engine, and more specifically to a turbine stator vane with an insert and a flexible or compliant seal.
  • a hot gas stream generated in a combustor is passed through a turbine to produce mechanical work.
  • the turbine includes one or more rows or stages of stator vanes and rotor blades that react with the hot gas stream in a progressively decreasing temperature.
  • the efficiency of the turbine - and therefore the engine - can be increased by passing a higher temperature gas stream into the turbine.
  • the turbine inlet temperature is limited to the material properties of the turbine, especially the first stage vanes and blades, and an amount of cooling capability for these first stage airfoils.
  • Turbine stator vanes are often cooled using impingement cooling inserts because the stator vanes do not rotate and thus an insert can be used.
  • High thermal stress occurs in first and even second stage stator vanes, and thus an insert would undergo relatively high movement within the cavity of the airfoil.
  • a flexible seal can be used to maintain a seal even under these relatively large displacements between the insert and the airfoil.
  • too much relative movement between the insert and the airfoil cavity would affect the seal performance.
  • a turbine stator vane with an impingement cooling insert with a flexible seal used to provide for a seal between the insert and the cavity of the airfoil, and where seal slots include bumper surfaces to limit a range of relative movement between the insert and the airfoil cavity so that the flexible seal continues to maintain a good seal.
  • an airfoil in one embodiment, includes a rib forming a forward impingement cavity and an aft impingement cavity each having an impingement cooling insert located therein.
  • Each insert and cavity includes a forward seal slot and an aft seal slot with a flexible seal secured therein.
  • Each seal slot includes a chordwise movement bumper and a sideways movement bumper with a gap to allow for a range of movement of the insert within the cavity while the flexible seal still maintains a seal.
  • the flexible seal is X-shaped with four contact points on the seal slots so that a relatively large but limited movement between the insert and the cavity can occur.
  • Another embodiment of the present invention includes a double impingement cooling insert having a pressure side surface and a suction side surface that forms a cooling air supply cavity, and where an arrangement of cross-over tubes connect return air holes on the pressure side of the insert to impingement holes on the suction side of the insert. Cooling air supplied to the supply cavity thus flows out through pressure side impingement holes to impinge on the pressure side surface of the airfoil, then flows through return air holes that are connected to the cross-over tubes.
  • the cross-over tubes are connected to impingement cooling holes on the suction side of the insert for impingement cooling of the suction side wall of the airfoil. With the cross-over tubes, the impingement cooling holes can be made as close together as possible depending on the diameter of the cross-over tubes.
  • Figure 1 shows a schematic view of a top section of a stator vane airfoil with two inserts secured inside with four flexible seals of the present invention
  • Figure 2 shows a schematic view of a top section of a forward insert and an aft insert each with two flexible seals of the present invention
  • Figure 3 shows a cross section top view of an airfoil wall and a forward insert with a flexible seal secured within slots having bumper surfaces of the present invention
  • Figure 4 shows a cross section top view of an airfoil wall and an aft insert with a flexible seal secured within slots having bumper surfaces of the present invention
  • Figure 5 shows a cross section top view of an airfoil wall with the forward insert and the aft insert secured within slots having bumper surfaces of the present invention.
  • the present invention is a turbine stator vane, such as a large frame industrial engine turbine stator vane, with impingement cooling inserts secured within the airfoil and sealed using a flexible or compliant seal, where the seal slots have bumper surfaces between the insert and the airfoil inner wall that limit relative movement of the seal slots so that the flexible seal maintains an adequate seal between the two surfaces.
  • the flexible seal used in the present invention is disclosed in U.S. Pat. No. 8,556,578, issued on October 15, 2013, to Memmen et al., which entire patent is incorporated herein by reference.
  • the flexible seal allows for a proper seal to be maintained between seal slots formed in the airfoil wall and the insert that will allow a large relative displacement where the prior art seals will not keep a seal.
  • One major feature missing from the Memmen patent is structure to limit the relative movements of the seal slots for a single flexible seal. The present invention solves this problem.
  • Figure 1 shows an embodiment of a stator vane with an airfoil 11 having a forward cavity with a forward impingement cooling insert 12 and an aft cavity with an aft impingement cooling insert 13.
  • Each impingement insert produces a sequential impingement or series of impingement of the airfoil walls.
  • impingement cooling occurs on the pressure side wall 9 and then on the suction side wall 10.
  • the cooling air pressure will be higher on the pressure side wall 9 than on the suction side wall 10, and thus seals are required to seal the pressure side impingement cavity from the suction side impingement cavity.
  • the forward impingement cooling insert 12 includes a forward flexible seal 14A and an aft flexible seal 14B.
  • the aft impingement insert 13 also includes a forward flexible seal 14C and an aft flexible seal 14D as seen in Figure 1.
  • FIG. 2 shows a top section of the forward insert 12 and the aft insert 13 with each insert having two flexible seals 14A-D.
  • Cross-over tubes 27 connect the pressure side impingement cavity to the suction side impingement cavity.
  • the aft insert 13 will also include these cross-over tubes. Cooling air is supplied to the interior each insert and then flows out through an arrangement of impingement cooling holes 29 on the pressure side to impinge against a backside surface of the pressure side wall of the airfoil 11. The spent impingement cooling air then flows through the cross-over tubes 27 and then through impingement cooling holes to impinge on the backside surface of the suction side wall of the airfoil 1 1.
  • the cross-over tubes 27 in the insert allows for a lightweight double impingement insert to be formed. Also, using the cross-over tubes 27 will allow for the impingement cooling holes on both the pressure side and the suction side of the insert to be closely spaced. This limitation in how close the impingement holes can be located will depend on the diameter of the cross-over tubes 27.
  • the multiple impingement insert with cross-over tubes 27 can also be manufactured using one of the additive manufacturing processes such as direct metal sintering, electron beam welding, or other 3D metal printing processes to produce a one-piece insert with the cross-over tubes.
  • the impingement holes 29 can also be formed from the metal additive manufacturing process which will further reduce cost of manufacturing because EDM drilling of the holes is quite expensive.
  • Figure 3 shows a cross section top view of the forward insert 12 with a forward seal slot between the leading edge surface of the airfoil 1 1 and a forward side of the forward insert 12.
  • An airfoil slot portion 16 is formed in the airfoil 11 and an insert slot portion 17 is formed in the insert 12, with the flexible seal 14A being located within the slot formed by the first 16 and second 17 slot portions. Because the cooled insert is at a much lower temperature than the airfoil during a steady state operation of the vane in an engine, the airfoil slot portion 16 and the insert slot portion 17 will have a great movement relative to each other. Too much of a relative movement will cause the flexible seal to leak. Therefore, the present invention includes structure to limit the relative movement of the slots.
  • two bumper surfaces (a first bumper surface 18A on the insert 12 and a corresponding second bumper surface 18B on the airfoil 1 1) will limit a sideways movement, while two bumper surfaces (a first bumper surface 19A on the insert 12 and a corresponding second bumper surface 19B on the airfoil 1 1 ) will limit a chordwise movement. Any space formed between bumper surfaces will depend on the flexibility of the seal 14.
  • Figure 4 shows a flexible seal 14D secured within a slot between an aft side of the aft insert 13 and airfoil 1 1.
  • Bumper surfaces 21 A, 21B formed on the insert 13 and the airfoil 1 1, respectively, will limit sideways movement while bumpers 22A, 22B formed on the insert 13 and the airfoil 1 1, respectively, will limit a chordwise movement between seal slot portions.
  • the seal slot in the airfoil extends from a pressure side wall of the airfoil 1 1.
  • a slot 15 for discharge of film cooling air is show along the pressure side wall of the airfoil 1 1.
  • Figure 5 shows a rib 28 formed between the forward cavity and the aft cavity of the airfoil in which the forward insert 12 and the aft insert 13 are sealed with a flexible seal 14B and 14C, respectively.
  • the forward insert 12 includes bumper surfaces 23 A, 23B formed on the insert 12 and the airfoil 11 , respectively, to limit a sideways movement and bumper surfaces 24A, 24B formed on the insert 12 and the airfoil 1 1, respectively, to limit a chordwise movement. Similar structure is formed for the aft insert 13.
  • Bumper surfaces 25 A, 25B formed on the insert 13 and the airfoil 1 1 respectively, limit sideways movement while bumper surfaces 26A, 26B formed on the insert 13 and the airfoil 1 1, respectively, limit a chordwise movement.
  • Figure 5 also shows a discharge slot 15 on the suction side wall of the airfoil 1 1. As seen in Figures 3 and 5, each seal slot has two bumper surfaces to limit sideways movement and two bumper surfaces to limit chordwise movement. In Figure 4, two bumper surfaces 22A, 22B are formed to limit chordwise movement.
  • the suction side wall 10 of the airfoil 1 1 includes a circular shaped bumper 21B (and the aft insert 13 includes bumper 21 A) while the pressure side wall 9 has a flat bumper surface 22B like the other seals of the airfoil.
  • This structure is due to the seal slots being formed upstream from the trailing edge and without a rib extending across the airfoil from the pressure side wall to the suction side wall.
  • the flexible seal 14 must maintain a seal between slots that have a large relative movement in order to prevent high pressure cooling air from crossing over the seal into the lower pressure cooling air and thus disrupt the series of impingement cooling from the pressure side to the suction side of the airfoil.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

An air cooled turbine stator vane with an impingement cooling insert (12,13) secured within a cavity, where a forward and an aft seal slot are formed between a backside surface of an airfoil and the impingement cooling insert in which flexible seals (14) are located, and where the backside surface of the airfoil and the insert include chordwise (19, 22, 24, 26) and sideways bumper surfaces (18, 21, 23, 25) each having a gap to allow for relative movement of the insert within the cavity from thermal gradients while maintaining a seal between the airfoil and the impingement cooling insert. Each flexible seal has an X-shaped cross-section having four points that each makes contact with a surface of the respective seal slot so that a high relative movement of the impingement cooling insert within the cavity can occur while still maintaining a tight seal. The impingement cooling insert includes a number of crossover tubes (27) connecting return air holes on a pressure side to impingement holes on a suction side of the impingement cooling insert.

Description

AIR COOLED TURBINE STATOR VANES
TECHNICAL FIELD
The present invention relates generally to a gas turbine engine, and more specifically to a turbine stator vane with an insert and a flexible or compliant seal.
BACKGROUND
In a gas turbine engine, such as a large frame heavy-duty industrial gas turbine (IGT) engine, a hot gas stream generated in a combustor is passed through a turbine to produce mechanical work. The turbine includes one or more rows or stages of stator vanes and rotor blades that react with the hot gas stream in a progressively decreasing temperature. The efficiency of the turbine - and therefore the engine - can be increased by passing a higher temperature gas stream into the turbine. However, the turbine inlet temperature is limited to the material properties of the turbine, especially the first stage vanes and blades, and an amount of cooling capability for these first stage airfoils.
Turbine stator vanes are often cooled using impingement cooling inserts because the stator vanes do not rotate and thus an insert can be used. High thermal stress occurs in first and even second stage stator vanes, and thus an insert would undergo relatively high movement within the cavity of the airfoil. A flexible seal can be used to maintain a seal even under these relatively large displacements between the insert and the airfoil. However, too much relative movement between the insert and the airfoil cavity would affect the seal performance. SUMMARY
A turbine stator vane with an impingement cooling insert, with a flexible seal used to provide for a seal between the insert and the cavity of the airfoil, and where seal slots include bumper surfaces to limit a range of relative movement between the insert and the airfoil cavity so that the flexible seal continues to maintain a good seal.
In one embodiment, an airfoil includes a rib forming a forward impingement cavity and an aft impingement cavity each having an impingement cooling insert located therein. Each insert and cavity includes a forward seal slot and an aft seal slot with a flexible seal secured therein. Each seal slot includes a chordwise movement bumper and a sideways movement bumper with a gap to allow for a range of movement of the insert within the cavity while the flexible seal still maintains a seal. The flexible seal is X-shaped with four contact points on the seal slots so that a relatively large but limited movement between the insert and the cavity can occur.
Another embodiment of the present invention includes a double impingement cooling insert having a pressure side surface and a suction side surface that forms a cooling air supply cavity, and where an arrangement of cross-over tubes connect return air holes on the pressure side of the insert to impingement holes on the suction side of the insert. Cooling air supplied to the supply cavity thus flows out through pressure side impingement holes to impinge on the pressure side surface of the airfoil, then flows through return air holes that are connected to the cross-over tubes. The cross-over tubes are connected to impingement cooling holes on the suction side of the insert for impingement cooling of the suction side wall of the airfoil. With the cross-over tubes, the impingement cooling holes can be made as close together as possible depending on the diameter of the cross-over tubes.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 shows a schematic view of a top section of a stator vane airfoil with two inserts secured inside with four flexible seals of the present invention;
Figure 2 shows a schematic view of a top section of a forward insert and an aft insert each with two flexible seals of the present invention;
Figure 3 shows a cross section top view of an airfoil wall and a forward insert with a flexible seal secured within slots having bumper surfaces of the present invention;
Figure 4 shows a cross section top view of an airfoil wall and an aft insert with a flexible seal secured within slots having bumper surfaces of the present invention; and
Figure 5 shows a cross section top view of an airfoil wall with the forward insert and the aft insert secured within slots having bumper surfaces of the present invention. DETAILED DESCRIPTION
The present invention is a turbine stator vane, such as a large frame industrial engine turbine stator vane, with impingement cooling inserts secured within the airfoil and sealed using a flexible or compliant seal, where the seal slots have bumper surfaces between the insert and the airfoil inner wall that limit relative movement of the seal slots so that the flexible seal maintains an adequate seal between the two surfaces. The flexible seal used in the present invention is disclosed in U.S. Pat. No. 8,556,578, issued on October 15, 2013, to Memmen et al., which entire patent is incorporated herein by reference. The flexible seal allows for a proper seal to be maintained between seal slots formed in the airfoil wall and the insert that will allow a large relative displacement where the prior art seals will not keep a seal. One major feature missing from the Memmen patent is structure to limit the relative movements of the seal slots for a single flexible seal. The present invention solves this problem.
Figure 1 shows an embodiment of a stator vane with an airfoil 11 having a forward cavity with a forward impingement cooling insert 12 and an aft cavity with an aft impingement cooling insert 13. Each impingement insert produces a sequential impingement or series of impingement of the airfoil walls. In this embodiment, impingement cooling occurs on the pressure side wall 9 and then on the suction side wall 10. The cooling air pressure will be higher on the pressure side wall 9 than on the suction side wall 10, and thus seals are required to seal the pressure side impingement cavity from the suction side impingement cavity. In one embodiment, the forward impingement cooling insert 12 includes a forward flexible seal 14A and an aft flexible seal 14B. The aft impingement insert 13 also includes a forward flexible seal 14C and an aft flexible seal 14D as seen in Figure 1.
Figure 2 shows a top section of the forward insert 12 and the aft insert 13 with each insert having two flexible seals 14A-D. Cross-over tubes 27 connect the pressure side impingement cavity to the suction side impingement cavity. The aft insert 13 will also include these cross-over tubes. Cooling air is supplied to the interior each insert and then flows out through an arrangement of impingement cooling holes 29 on the pressure side to impinge against a backside surface of the pressure side wall of the airfoil 11. The spent impingement cooling air then flows through the cross-over tubes 27 and then through impingement cooling holes to impinge on the backside surface of the suction side wall of the airfoil 1 1.
Use of the cross-over tubes 27 in the insert allows for a lightweight double impingement insert to be formed. Also, using the cross-over tubes 27 will allow for the impingement cooling holes on both the pressure side and the suction side of the insert to be closely spaced. This limitation in how close the impingement holes can be located will depend on the diameter of the cross-over tubes 27. The multiple impingement insert with cross-over tubes 27 can also be manufactured using one of the additive manufacturing processes such as direct metal sintering, electron beam welding, or other 3D metal printing processes to produce a one-piece insert with the cross-over tubes. The impingement holes 29 can also be formed from the metal additive manufacturing process which will further reduce cost of manufacturing because EDM drilling of the holes is quite expensive.
Figure 3 shows a cross section top view of the forward insert 12 with a forward seal slot between the leading edge surface of the airfoil 1 1 and a forward side of the forward insert 12. An airfoil slot portion 16 is formed in the airfoil 11 and an insert slot portion 17 is formed in the insert 12, with the flexible seal 14A being located within the slot formed by the first 16 and second 17 slot portions. Because the cooled insert is at a much lower temperature than the airfoil during a steady state operation of the vane in an engine, the airfoil slot portion 16 and the insert slot portion 17 will have a great movement relative to each other. Too much of a relative movement will cause the flexible seal to leak. Therefore, the present invention includes structure to limit the relative movement of the slots. In Figure 3, two bumper surfaces (a first bumper surface 18A on the insert 12 and a corresponding second bumper surface 18B on the airfoil 1 1) will limit a sideways movement, while two bumper surfaces (a first bumper surface 19A on the insert 12 and a corresponding second bumper surface 19B on the airfoil 1 1 ) will limit a chordwise movement. Any space formed between bumper surfaces will depend on the flexibility of the seal 14.
Figure 4 shows a flexible seal 14D secured within a slot between an aft side of the aft insert 13 and airfoil 1 1. Bumper surfaces 21 A, 21B formed on the insert 13 and the airfoil 1 1, respectively, will limit sideways movement while bumpers 22A, 22B formed on the insert 13 and the airfoil 1 1, respectively, will limit a chordwise movement between seal slot portions. In the Figure 4 embodiment, the seal slot in the airfoil extends from a pressure side wall of the airfoil 1 1. A slot 15 for discharge of film cooling air is show along the pressure side wall of the airfoil 1 1.
Figure 5 shows a rib 28 formed between the forward cavity and the aft cavity of the airfoil in which the forward insert 12 and the aft insert 13 are sealed with a flexible seal 14B and 14C, respectively. The forward insert 12 includes bumper surfaces 23 A, 23B formed on the insert 12 and the airfoil 11 , respectively, to limit a sideways movement and bumper surfaces 24A, 24B formed on the insert 12 and the airfoil 1 1, respectively, to limit a chordwise movement. Similar structure is formed for the aft insert 13. Bumper surfaces 25 A, 25B formed on the insert 13 and the airfoil 1 1 , respectively, limit sideways movement while bumper surfaces 26A, 26B formed on the insert 13 and the airfoil 1 1, respectively, limit a chordwise movement. Figure 5 also shows a discharge slot 15 on the suction side wall of the airfoil 1 1. As seen in Figures 3 and 5, each seal slot has two bumper surfaces to limit sideways movement and two bumper surfaces to limit chordwise movement. In Figure 4, two bumper surfaces 22A, 22B are formed to limit chordwise movement. To limit sideways movement, the suction side wall 10 of the airfoil 1 1 includes a circular shaped bumper 21B (and the aft insert 13 includes bumper 21 A) while the pressure side wall 9 has a flat bumper surface 22B like the other seals of the airfoil. This structure is due to the seal slots being formed upstream from the trailing edge and without a rib extending across the airfoil from the pressure side wall to the suction side wall.
The flexible seal 14 must maintain a seal between slots that have a large relative movement in order to prevent high pressure cooling air from crossing over the seal into the lower pressure cooling air and thus disrupt the series of impingement cooling from the pressure side to the suction side of the airfoil.

Claims

What is claimed is:
1. An air cooled turbine stator vane comprising:
an airfoil with a leading edge region and a trailing edge region and a pressure side wall and a suction side wall;
the airfoil being a hollow airfoil forming a cavity;
a seal slot opening into the cavity;
an impingement cooling insert located within the cavity and having a seal slot facing the seal slot on the cavity;
a chordwise movement bumper formed on the cavity and on the insert to limit a chordwise movement of the impingement cooling insert relative to the cavity;
a sideways movement bumper formed on the cavity and on the insert to limit a sideways movement of the impingement cooling insert relative to the cavity;
a flexible seal secured within the seal slots of the cavity and the insert;
a chordwise gap formed between the chordwise movement bumpers and a sideways gap formed between the sideways movement bumpers such that the flexible seal can maintains a seal between the cavity and the impingement cooling insert due to relative movement from thermal gradients.
2. The air cooled turbine stator vane of claim 1 , wherein:
the hollow airfoil includes a rib separating a forward cavity from an aft cavity; each cavity includes a forward seal slot and an aft seal slot formed between an impingement cooling insert;
each forward seal slot and aft seal slot includes a chordwise movement bumper and a sideways movement bumper;
a flexible seal is secured within each of the forward seal slots and the aft seal slots; and
a gap is formed between the chordwise movement bumper and a
corresponding sideways movement bumper so that the flexible seals maintain a seal between the cavity and the insert due to relative movement from thermal gradients.
3. The air cooled turbine stator vane of claim 2, wherein the rib includes an aft seal slot for the forward cavity and a forward seal slot for the aft cavity.
4. The air cooled turbine stator vane of claim 1 , wherein the flexible seal is an X- shaped seal with four points that each makes contact with a surface of the seal slots.
5. An air cooled turbine stator vane comprising:
an airfoil with a hollow cavity;
an impingement cooling insert secured within the hollow cavity of the airfoil; the impingement cooling insert having a pressure side surface and a suction side surface enclosing a cooling air supply cavity;
the pressure side surface having an arrangement of pressure side impingement cooling holes connected to the cooling air supply cavity;
the pressure side surface having an arrangement of return air holes;
the suction side surface having an arrangement of suction side impingement cooling holes; and
the impingement cooling insert having a plurality of cross-over tubes that connect the return air holes on the pressure side surface to the impingement cooling air holes on the suction side surface.
6. The air cooled turbine stator vane of claim 5, wherein the impingement cooling insert includes a forward seal slot and an aft seal slot, and the air cooled turbine stator vane further comprising a flexible seal secured within each of the forward seal slot and the aft seal slot to produce a seal between cooling air on the pressure side and the suction side of the insert.
7. The air cooled turbine stator vane of claim 5, wherein each of the forward seal slot and the aft seal slot includes a chordwise movement bumper surface and a sideways movement bumper surface to limit a relative movement of the insert with respect to the hollow cavity of the airfoil such that the flexible seal maintains a seal.
8. The air cooled turbine stator vane of claim 6, wherein the flexible seal is an X- shaped seal having four contact surfaces within a seal slot.
EP16710066.8A 2016-03-04 2016-03-04 Air cooled turbine stator vanes Withdrawn EP3423680A1 (en)

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PCT/US2016/020945 WO2017151146A1 (en) 2016-03-04 2016-03-04 Air cooled turbine stator vanes

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Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9353631B2 (en) * 2011-08-22 2016-05-31 United Technologies Corporation Gas turbine engine airfoil baffle
US8556578B1 (en) 2012-08-15 2013-10-15 Florida Turbine Technologies, Inc. Spring loaded compliant seal for high temperature use
US8500405B1 (en) * 2012-09-20 2013-08-06 Florida Turbine Technologies, Inc. Industrial stator vane with sequential impingement cooling inserts
US9611755B2 (en) * 2013-11-20 2017-04-04 Florida Turbine Technologies, Inc. Turbine stator vane with insert and flexible seal

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