EP2201220A1 - A method of producing a rotor component or a stator component - Google Patents

A method of producing a rotor component or a stator component

Info

Publication number
EP2201220A1
EP2201220A1 EP07808812A EP07808812A EP2201220A1 EP 2201220 A1 EP2201220 A1 EP 2201220A1 EP 07808812 A EP07808812 A EP 07808812A EP 07808812 A EP07808812 A EP 07808812A EP 2201220 A1 EP2201220 A1 EP 2201220A1
Authority
EP
European Patent Office
Prior art keywords
ring
intermediate ring
external
operative position
disc
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Withdrawn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
EP07808812A
Other languages
German (de)
French (fr)
Inventor
Bengt Derehag
Staffan Brodin
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.)
GKN Aerospace Sweden AB
Original Assignee
Volvo Aero AB
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 Volvo Aero AB filed Critical Volvo Aero AB
Publication of EP2201220A1 publication Critical patent/EP2201220A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the present invention relates to method of producing a rotor component or a stator component. More particularly, the component comprises a disc-shaped element with a plurality of raclially projecting and circumferentialIy spaced air foil projections, or blades .
  • the invention aims for attaching a ring-shaped band, or shroud, radially outside and in interfering contact with the blade tips .
  • the shroud is adapted to counteract leakage from a pressure side to a suction side of the blade and vibrations during operation. Such leakage is associated with efficiency losses, and the vibrations are associated with an increase in fatigue cracks.
  • the invention is not to be regarded as being limited to this use but can also be used in other applications .
  • the component can be used in both static applications (stators) and dynamic applications (rotors) .
  • the component can also find application in both turbines and compressors.
  • the component is commonly referred to as a "blisk” (blade integrated disk) or a "bling" (bladed ring) .
  • the blade is often called a guide vane when applied in stators and is intended in operation to guide or deflect a gas flow.
  • the blade When applied in rotors, the blade is usually used for both guiding and power transmission.
  • the stator component or rotor component can, for example, be arranged in a gas turbine or jet engine.
  • the areas of application of the component are, for example, in engines for vehicles, aircraft, power plant equipment for vessels and power stations for electricity production.
  • the purpose of the invention is to achieve a cost- efficient manufacturing of a stator component or rotor component, and especially for applying a shroud radially outside of a disc-shaped element with a plurality of radially projecting and circumferentially spaced blades.
  • the method especially aims for creating conditions for a final weight reduction of the component.
  • the purpose is achieved by the method defined in claim 1.
  • a method comprising the steps of - providing a disc-shaped element with a plurality of radially projecting and circumferentially spaced blades, an intermediate ring with an inner surface adapted for contacting tips of said blades, and an external ring with an inner surface adapted for contacting an outer surface of the intermediate ring,
  • the external ring comprises a composite structure. This feature creates conditions for a weight reduction and a high tensile strength of the final component. Further, it can be operated in higher speed ranges due to the lower weight of the external ring.
  • the external ring preferably comprises the composite structure prior to the assembly of the ring to the disc-shaped element. According to a preferred alternative, carbon fibres are used in the composite structure.
  • the intermediate ring comprises a metal material .
  • the intermediate ring is preferably substantially thinner than the external ring.
  • the thickness of the intermediate ring is preferably less than 50% and especially less than 25% of the thickness of the external ring.
  • the intermediate ring creates conditions for an improved assembly of the external composite ring.
  • the method comprises the steps of providing the intermediate ring with excess material adapted for providing the intermediate ring with an increased rigidity during said movement, and moving the intermediate ring with the excess material in relation to the disc-shaped element to said operative position.
  • the excess material creates conditions for a further improved assembly of the external composite ring. This is especially advantageous when the excess material is provided with an external conical surface for interaction with the external ring during said relative movement. After having positioned the intermediate ring in said operative position, the excess material is removed.
  • FIG 1 shows a disc-shaped element in a perspective view
  • FIG- -2 shows a first manufacturing step in- a -cut view, wherein an intermediate ring is applied on the disc-shaped element
  • FIG 3 shows a second manufacturing step in a cut view, wherein an external ring is applied on the intermediate ring
  • FIG 4 shows the external ring in its operative position in a cut view, wherein excess material has been removed from the intermediate ring in a third manufacturing step
  • FIG 5 shows an enlarged cross section view of the disc shaped element provided with the external ring in its operative position.
  • Figure 1 shows a disc-shaped element 1, which comprises a central part 2, what is known as a hub, and a plurality of circumferentially spaced blades 3 which are arranged on a circular path and projecting in the radial direction from the hub. Thus, the blades 3 are attached to the hub 2.
  • Each of the blades 3 has a blade root 4 and a blade tip 5 disposed opposite the root, see figure 2.
  • Figures 2-4 show consecutive manufacturing steps for attaching a shroud 10 (external ring) to the blades 3.
  • a work piece 6 comprises a first part 7, which is configured to form a continuous intermediate ring and a second annular part 8 forming excess material to be removed later.
  • the excess material 8 is adapted for providing the intermediate ring with an increased rigidity during assembly. In other words, the excess material is adapted so that the intermediate ring will sustain an application force during assembly.
  • the excess material 8 is unitary with the intermediate ring.
  • the excess material 8 is in one piece with the intermediate ring 7.
  • the intermediate ring 7 comprises a metal material, preferably a lightweight material such as titanium or aluminium.
  • the intermediate ring 7 forms a supporting metal ring.
  • the intermediate ring 7 comprises a cylindrical inner surface adapted for contacting the blade tips 5 of the disc-shaped element 1.
  • the method comprises the step of moving the work piece 6 (comprising the intermediate ring 7) co-axially in relation to the disc-shaped element 1 to an operative position, in which it is located radially outside the blades 3.
  • the axial movement is illustrated by means of an arrow.
  • the method comprises the step of moving the intermediate ring 7 with the excess material in relation to the disc-shaped element 1 to said operative position.
  • the second part (the excess material) 8 is provided with an external conical surface 9 (tapered surface) for interaction with the external ring 10 during a next step.
  • a continuous external ring 10 preferably comprises a composite structure 17, see figure 6.
  • the composite structure 17 comprises a circumferentially wound fibre structure.
  • the composite material is lightweight, has a high strength and stiffness and a low coefficient of thermal expansion.
  • Composite materials can provide a ring which is self-supporting ⁇ atr ⁇ very "high rotational speeds while minimizing its radial thermal growth .
  • the external ring 10 is provided with an inner surface 12 adapted for contacting an outer surface of the intermediate ring 7.
  • the external ring 10 is provided with an inner diameter substantially equal to an outer diameter of the intermediate ring 7.
  • the method comprises the step of moving the external ring 10 co-axially in relation to the intermediate ring 7 to an operative position, in which it is located radially outside the intermediate ring. More specifically, the method comprises the step of applying a pressure in an axial direction on the external ring 10 in order to move it to said operative position. A separate annular pressure application means 11 is used for applying the pressure on the external ring.
  • the method comprises the sequential steps of first moving the intermediate ring 7 co-axially in relation to the disc-shaped element 1 to its operative position and then moving the external ring 10 co-axially in relation to the intermediate ring 7 to its operative position.
  • the method preferably comprises the step of providing the pressure application means 11 with an internal conical surface configured for interaction with the external conical surface of the excess material 8 during said movement.
  • the method comprises the step of moving the external ring 10 while the fibre structure 17 is in a preloaded state.
  • the method preferably comprises the step of providing an adhesive (preferably glue) on the contacting surfaces of the external ring 10 and the intermediate ring 7.
  • an adhesive preferably glue
  • the adhesive also forms a lubrication during assembly.
  • the method further comprises the step of removing the excess material 8 after having positioned the external ring 10 radially outside the intermediate ring 7. This removed excess material is indicated with phantom lines in figure 4. More specifically, the method comprises the step of removing the excess material 8 after having positioned the intermediate ring 7 in said operative position relative to the disc-shaped element 1.
  • the extra material 8 is preferably removed in a machining process .
  • FIG 4 shows the external ring 10 applied in its operative position radially outside and in interfering contact with the intermediate ring 14.
  • the excess material 8 has been removed in figure 4.
  • the external ring 10 is held in place by interfering contact.
  • Figure 5 shows a cross section view of the final rotor comprising the external ring 10.
  • the external ring 10 comprises a composite fibre structure 17.
  • the fibres are preferably glued together.
  • the composite fibre structure 17 may comprise an OMC (Organic Matrix composite material) or MMC (metal matric composite material) .
  • OMC comprises a thermosetting resin, such as an epoxy, polyester or polyamide, and usually cures or hardens in the • presence ⁇ of a catalyst, such as heat or pressure.
  • the matrix component of an OMC can be provided in the form of a thermoplastic resin, such as polycarbonate or polysulfone.
  • the matrix component of an MMC material may comprise metals such as aluminium, titanium, titanium aluminide and the like.
  • the fibres of OMC and MMC are typically formed from boron, graphite or carbide .
  • the external ring may first be applied radially outside the intermediate ring and therafter, they may in unison be applied on the disc-shaped element.
  • the blade tips may be provided with an external conical surface (tapered surface) for interaction with the intermediate ring during assembly.
  • the intermediate ring may be provided with an internal conical surface (tapered surface) for interaction with the blade tips during assembly.

Landscapes

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

Abstract

The invention relates to a method of producing a rotor component or a stator component, comprising the steps of - providing a disc-shaped element (1) with a plurality of radially projecting and circumferential Iy spaced blades (3), an intermediate ring (7) with an inner surface adapted for contacting tips (5) of said blades, and an external ring (10) with an inner surface adapted for contacting an outer surface of the intermediate ring (7), moving the intermediate ring (7) co-axially in relation to the disc-shaped element (1) to an operative position, in which it is located radially outside the blades (3), and - moving the external ring (10) co-axially in relation to the intermediate ring (7) to an operative position, in which it is located radially outside the intermediate ring.

Description

A method of producing a rotor component or a stator component
FIELD OF THE INVENTION
The present invention relates to method of producing a rotor component or a stator component. More particularly, the component comprises a disc-shaped element with a plurality of raclially projecting and circumferentialIy spaced air foil projections, or blades . The invention aims for attaching a ring-shaped band, or shroud, radially outside and in interfering contact with the blade tips .
The shroud is adapted to counteract leakage from a pressure side to a suction side of the blade and vibrations during operation. Such leakage is associated with efficiency losses, and the vibrations are associated with an increase in fatigue cracks. The invention is not to be regarded as being limited to this use but can also be used in other applications .
The component can be used in both static applications (stators) and dynamic applications (rotors) . The component can also find application in both turbines and compressors. For rotors, the component is commonly referred to as a "blisk" (blade integrated disk) or a "bling" (bladed ring) . The blade is often called a guide vane when applied in stators and is intended in operation to guide or deflect a gas flow. When applied in rotors, the blade is usually used for both guiding and power transmission. The stator component or rotor component can, for example, be arranged in a gas turbine or jet engine. The areas of application of the component are, for example, in engines for vehicles, aircraft, power plant equipment for vessels and power stations for electricity production.
SUMMARY OF THE INVENTION
The purpose of the invention is to achieve a cost- efficient manufacturing of a stator component or rotor component, and especially for applying a shroud radially outside of a disc-shaped element with a plurality of radially projecting and circumferentially spaced blades. The method especially aims for creating conditions for a final weight reduction of the component.
This purpose is achieved by the method defined in claim 1. Thus, the purpose is achieved by a method comprising the steps of - providing a disc-shaped element with a plurality of radially projecting and circumferentially spaced blades, an intermediate ring with an inner surface adapted for contacting tips of said blades, and an external ring with an inner surface adapted for contacting an outer surface of the intermediate ring,
- moving the intermediate ring co-axially in relation to the disc-shaped element to an operative position, in which it is located radially outside the blades, and
- moving the external ring co-axially in relation to the intermediate ring to an operative position, in which it is located radially outside the intermediate ring.
According to a preferred embodiment, the external ring comprises a composite structure. This feature creates conditions for a weight reduction and a high tensile strength of the final component. Further, it can be operated in higher speed ranges due to the lower weight of the external ring. The external ring preferably comprises the composite structure prior to the assembly of the ring to the disc-shaped element. According to a preferred alternative, carbon fibres are used in the composite structure.
According to a further preferred " embodiment , the intermediate ring comprises a metal material . The intermediate ring is preferably substantially thinner than the external ring. The thickness of the intermediate ring is preferably less than 50% and especially less than 25% of the thickness of the external ring. The intermediate ring creates conditions for an improved assembly of the external composite ring.
According to a further preferred embodiment, the method comprises the steps of providing the intermediate ring with excess material adapted for providing the intermediate ring with an increased rigidity during said movement, and moving the intermediate ring with the excess material in relation to the disc-shaped element to said operative position. The excess material creates conditions for a further improved assembly of the external composite ring. This is especially advantageous when the excess material is provided with an external conical surface for interaction with the external ring during said relative movement. After having positioned the intermediate ring in said operative position, the excess material is removed. Other advantageous features and functions of various embodiments of the invention are set forth in the following description and in the dependent claims .
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be explained below, with reference to the embodiments shown on the appended drawings , wherein FIG 1 shows a disc-shaped element in a perspective view, FIG- -2 shows a first manufacturing step in- a -cut view, wherein an intermediate ring is applied on the disc-shaped element,
FIG 3 shows a second manufacturing step in a cut view, wherein an external ring is applied on the intermediate ring,
FIG 4 shows the external ring in its operative position in a cut view, wherein excess material has been removed from the intermediate ring in a third manufacturing step, FIG 5 shows an enlarged cross section view of the disc shaped element provided with the external ring in its operative position.
DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS OF THE INVENTION
Figure 1 shows a disc-shaped element 1, which comprises a central part 2, what is known as a hub, and a plurality of circumferentially spaced blades 3 which are arranged on a circular path and projecting in the radial direction from the hub. Thus, the blades 3 are attached to the hub 2. Each of the blades 3 has a blade root 4 and a blade tip 5 disposed opposite the root, see figure 2. Figures 2-4 show consecutive manufacturing steps for attaching a shroud 10 (external ring) to the blades 3.
A work piece 6 comprises a first part 7, which is configured to form a continuous intermediate ring and a second annular part 8 forming excess material to be removed later. The excess material 8 is adapted for providing the intermediate ring with an increased rigidity during assembly. In other words, the excess material is adapted so that the intermediate ring will sustain an application force during assembly.
The excess material 8 is unitary with the intermediate ring. In other words, the excess material 8 is in one piece with the intermediate ring 7. The intermediate ring 7 comprises a metal material, preferably a lightweight material such as titanium or aluminium. Thus, the intermediate ring 7 forms a supporting metal ring.
The intermediate ring 7 comprises a cylindrical inner surface adapted for contacting the blade tips 5 of the disc-shaped element 1. The method comprises the step of moving the work piece 6 (comprising the intermediate ring 7) co-axially in relation to the disc-shaped element 1 to an operative position, in which it is located radially outside the blades 3. The axial movement is illustrated by means of an arrow.
More specifically, the method comprises the step of moving the intermediate ring 7 with the excess material in relation to the disc-shaped element 1 to said operative position. The second part (the excess material) 8 is provided with an external conical surface 9 (tapered surface) for interaction with the external ring 10 during a next step.
A continuous external ring 10 (or shroud) preferably comprises a composite structure 17, see figure 6. The composite structure 17 comprises a circumferentially wound fibre structure. The composite material is lightweight, has a high strength and stiffness and a low coefficient of thermal expansion. Composite materials can provide a ring which is self-supporting~atr~very "high rotational speeds while minimizing its radial thermal growth .
The external ring 10 is provided with an inner surface 12 adapted for contacting an outer surface of the intermediate ring 7. The external ring 10 is provided with an inner diameter substantially equal to an outer diameter of the intermediate ring 7.
The method comprises the step of moving the external ring 10 co-axially in relation to the intermediate ring 7 to an operative position, in which it is located radially outside the intermediate ring. More specifically, the method comprises the step of applying a pressure in an axial direction on the external ring 10 in order to move it to said operative position. A separate annular pressure application means 11 is used for applying the pressure on the external ring.
Thus, the method comprises the sequential steps of first moving the intermediate ring 7 co-axially in relation to the disc-shaped element 1 to its operative position and then moving the external ring 10 co-axially in relation to the intermediate ring 7 to its operative position. The method preferably comprises the step of providing the pressure application means 11 with an internal conical surface configured for interaction with the external conical surface of the excess material 8 during said movement.
Preferably, the method comprises the step of moving the external ring 10 while the fibre structure 17 is in a preloaded state.
The method preferably comprises the step of providing an adhesive (preferably glue) on the contacting surfaces of the external ring 10 and the intermediate ring 7. In addition to providing a fastening function in the applied state, the adhesive also forms a lubrication during assembly.
The method further comprises the step of removing the excess material 8 after having positioned the external ring 10 radially outside the intermediate ring 7. This removed excess material is indicated with phantom lines in figure 4. More specifically, the method comprises the step of removing the excess material 8 after having positioned the intermediate ring 7 in said operative position relative to the disc-shaped element 1. The extra material 8 is preferably removed in a machining process .
Figure 4 shows the external ring 10 applied in its operative position radially outside and in interfering contact with the intermediate ring 14. The excess material 8 has been removed in figure 4. The external ring 10 is held in place by interfering contact. Figure 5 shows a cross section view of the final rotor comprising the external ring 10. The external ring 10 comprises a composite fibre structure 17. The fibres are preferably glued together. The composite fibre structure 17 may comprise an OMC (Organic Matrix composite material) or MMC (metal matric composite material) . OMC comprises a thermosetting resin, such as an epoxy, polyester or polyamide, and usually cures or hardens in the • presence ~ of a catalyst, such as heat or pressure. Alternatively, the matrix component of an OMC can be provided in the form of a thermoplastic resin, such as polycarbonate or polysulfone. The matrix component of an MMC material may comprise metals such as aluminium, titanium, titanium aluminide and the like. The fibres of OMC and MMC are typically formed from boron, graphite or carbide .
The invention is not in any way limited to the above described embodiments, instead a number of alternatives and modifications are possible without departing from the scope of the following claims .
For example, some of the method steps may be performed in a different order. According to one example, the external ring may first be applied radially outside the intermediate ring and therafter, they may in unison be applied on the disc-shaped element.
Further, the blade tips may be provided with an external conical surface (tapered surface) for interaction with the intermediate ring during assembly. According to an alternative, or complement, the intermediate ring may be provided with an internal conical surface (tapered surface) for interaction with the blade tips during assembly.

Claims

1. A method of producing a rotor component or a stator component, comprising the steps of
- providing a disc-shaped element (1) with a plurality of radially projecting and circumferentially spaced blades (3), an intermediate ring (7) with an inner surface adapted for contacting tips (5) of said blades, and an external ring (10) with an inner surface adapted for contacting an outer surface of the intermediate ring
(7), moving the intermediate ring (7) co-axially in relation to the disc-shaped element (1) to an operative position, in which it is located radially outside the blades (3) , and
- moving the external ring (10) co-axially in relation to the intermediate ring (7) to an operative position, in which it is located radially outside the intermediate ring .
2. A method according to claim 1 , wherein the external ring (10) comprises a composite structure (17) .
3. A method according to claim 2, wherein the composite structure (17) comprises a circumferentially wound fibre structure.
4. A method according to claim 3, comprising the step of moving the external ring (10) in relation to the intermediate ring while the fibre structure (17) is in a preloaded state.
5. A method according to any preceding claim, comprising the step of providing the external ring (10) with an inner diameter substantially equal to an outer diameter of the intermediate ring (7) . 5
6. A method according to any preceding claim, comprising the step of applying a pressure in an axial direction on the external ring (10) in order to move it to said operative position. -0
7. A method according to claim 6, using a separate pressure application means (11) for applying the pressure on the external ring. 5
8. A method according to any preceding claim, wherein the intermediate ring (7) comprises a metal material.
9. A method according to any preceding claim, comprising the steps of providing the intermediate ring (7) with 0 excess material (8) adapted for providing the intermediate ring with an increased rigidity during said movement, and moving the intermediate ring (7) with the excess material in relation to the disc-shaped element
(1) to said operative position. 5
10. A method according to claim 9, providing the excess material (8) with an external conical surface (9) for interaction with the external ring (10) during said relative movement . 0
11. A method according to claim 9 or 10, removing the excess material (8) after having positioned the external ring (10) radially outside the intermediate ring (7) .
12. A method according to any one of claims 9-11, removing the excess material (8) after having positioned the intermediate ring (7) in said operative position relative to the disc-shaped element (1) .
13. A method according to any preceding claim, comprising the sequential steps of first moving the intermediate ring (7) co-axially in relation to the disc-shaped element (1) to its operative position and then moving the external ring (10) co-axially in relation to the intermediate ring (7) to its operative position.
EP07808812A 2007-09-12 2007-09-12 A method of producing a rotor component or a stator component Withdrawn EP2201220A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2007/000800 WO2009035380A1 (en) 2007-09-12 2007-09-12 A method of producing a rotor component or a stator component

Publications (1)

Publication Number Publication Date
EP2201220A1 true EP2201220A1 (en) 2010-06-30

Family

ID=40452233

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07808812A Withdrawn EP2201220A1 (en) 2007-09-12 2007-09-12 A method of producing a rotor component or a stator component

Country Status (3)

Country Link
US (1) US20110056078A1 (en)
EP (1) EP2201220A1 (en)
WO (1) WO2009035380A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2521588A (en) * 2013-10-11 2015-07-01 Reaction Engines Ltd Turbine blades
DE102014203871A1 (en) * 2014-03-04 2015-09-10 Robert Bosch Gmbh Impeller for a turbine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB938123A (en) * 1960-05-19 1963-10-02 Studebaker Packard Corp Improvements in or relating to an axial flow compressor
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means
EP0219140A3 (en) * 1985-10-15 1988-09-21 The Boeing Company Single piece shroud for turbine rotor
US5059095A (en) * 1989-10-30 1991-10-22 The Perkin-Elmer Corporation Turbine rotor blade tip coated with alumina-zirconia ceramic
ATE426085T1 (en) * 2004-12-08 2009-04-15 Volvo Aero Corp WHEEL FOR A ROTARY FLOW MACHINE

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009035380A1 *

Also Published As

Publication number Publication date
WO2009035380A1 (en) 2009-03-19
US20110056078A1 (en) 2011-03-10

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