EP2252798A1 - Impeller and turbocharger - Google Patents

Impeller and turbocharger

Info

Publication number
EP2252798A1
EP2252798A1 EP08872443A EP08872443A EP2252798A1 EP 2252798 A1 EP2252798 A1 EP 2252798A1 EP 08872443 A EP08872443 A EP 08872443A EP 08872443 A EP08872443 A EP 08872443A EP 2252798 A1 EP2252798 A1 EP 2252798A1
Authority
EP
European Patent Office
Prior art keywords
impeller
backplate
downstream side
vane
radial direction
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08872443A
Other languages
German (de)
French (fr)
Other versions
EP2252798B1 (en
Inventor
Francis Heyes
Paul Roach
Ian Brown
Geoffrey Ngao
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.)
Napier Turbochargers Ltd
Original Assignee
Napier Turbochargers Ltd
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 Napier Turbochargers Ltd filed Critical Napier Turbochargers Ltd
Priority to EP08872443.0A priority Critical patent/EP2252798B1/en
Publication of EP2252798A1 publication Critical patent/EP2252798A1/en
Application granted granted Critical
Publication of EP2252798B1 publication Critical patent/EP2252798B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Definitions

  • the present invention relates to an impeller and a turbocharger .
  • An industrial turbocharger compressor impeller is typically made from aluminium. This material is relatively cheap, is easy to machine and is light enough so that turbo lag is not a major problem.
  • Current turbocharger impellers for medium speed diesel engines tend not to have a through bore since this minimises the stress in the impeller material and reduces the likelihood of the impeller failing due to fatigue during a typical 50,000 hour life.
  • Impeller creep failure is associated with areas of high stress and high temperature.
  • the area of highest temperature, and consequently the area which determines the creep life, is on the back of the impeller near the outer diameter. This is an area where typically a labyrinth seal is located to reduce the leakage of compressed air towards the bearings.
  • the high temperature is associated with windage heating in that area.
  • the impeller life must typically achieve 50,000 hours. This is achieved traditionally by limiting the operating speed of the turbocharger in line with calculations of the creep life. At lower operating speeds the impeller stresses are lower, the compressed air at the downstream side of the impeller is cooler, and the windage heating is less than at higher operating speed.
  • a combination of direct and indirect cooling of the flow in radial gaps formed between rotors and stators of turbine-type machines is disclosed, wherein a first cooling fluid, preferably water, is used for indirect cooling and a second gaseous cooling fluid, preferably air, is used for direct cooling.
  • a first cooling fluid preferably water
  • a second gaseous cooling fluid preferably air
  • the cooled air is typically taken from the diesel engine air manifold, after the compressed air has been cooled by the charge air cooler.
  • the introduction of this cooled air is a parasitic loss on the turbocharger efficiency, since the turbocharger has to compress the coolant air but the air is not used in the diesel engine.
  • this cooled air leaks into the main stream of the compressor flow between impeller and diffuser and will cause a disturbance to the flow which reduces the compressor efficiency. Nevertheless, by cooling the impeller the compressor is allowed to operate at higher speed while still achieving the required 50,000 hours life.
  • the first objective may be solved by an impeller as claimed in claim 1.
  • the second objective may be solved by a compressor as claimed in claim 11.
  • the third objective may be solved by a turbocharger as claimed in claim 12.
  • the depending claims define further developments of the invention.
  • An inventive impeller comprises a rotation axis, a radial direction, a backplate and a number of vanes which are connected to the backplate at a line of connection.
  • Each vane comprises an upstream side, a downstream side and an outer side.
  • the downstream side of each vane comprises an edge portion which is located near the outer side.
  • the vanes project radially over the backplate and the downstream side further comprises a connecting portion connecting the edge portion to the line of connection between the respective vane and the backplate and including an angle with the radial direction.
  • the radial projection of the vanes means that radially outer parts of the vanes are preserved, which helps to maintain the ability of the impeller to pressurise the flow.
  • the edge portion may be orientated perpendicular to the radial direction.
  • the connecting portion may have a convex rounded portion which is located near the connection line.
  • a convex rounded portion can extend from the edge portion to the line of connection between the respective vane and the backplate.
  • such a convex rounded portion can be part of an S-shape portion which may extend from the edge portion to the line of connection between the respective vane and the backplate.
  • each vane is backswept on moving in an airflow direction from its upstream side to its downstream side.
  • Backsweeping the vanes can introduce an extra tangential component into the flow leaving the impeller, which can improve flow stability and efficiency.
  • Backsweep can also increase bending stresses in the vanes, but advantageously these stresses can be reduced by employing a connecting portion which has a convex rounded portion located near the connection line.
  • a further advantage of employing a connecting portion which has a convex rounded portion located near the connection line is that the high centrifugal stresses which can be generated in the region where the vane and the backplate meet can be reduced.
  • a connecting portion which has an S-shape portion is particularly advantageous.
  • the backplate can comprise a radially outer peripheral surface and the connecting portion can be adjacent to the radially outer peripheral surface of the backplate.
  • the radially outer peripheral surface of the backplate may be located in a plane with a normal being locally parallel to the radial direction. This means, that the radially outer surface may run parallel to the rotation axis.
  • the radially outer peripheral surface of the backplate can be located in a plane with a normal which includes an angle between 0° and 45° with the radial direction.
  • the angle may have a value between 15° and 25°. This further reduces stress and temperature on the surface of the backplate .
  • the radially outer surface of the inventive impeller may especially be located at a radial position closer to the rotation axis than the radially outer surface of a conventional impeller.
  • the distance between the radially outer surface and the rotation axis of an inventive impeller is smaller than the distance between the radially outer surface and the rotation axis of a conventional impeller.
  • An angle between a tangent located at the connecting portion adjacent to the connection line and the radial direction may have a value between 10° and 45°, preferably between 15° and 25°. This reduces vane leakage losses.
  • the edge portion of the downstream side can have a length in the direction of the rotation axis of more than 50% of the length of the downstream side in the direction of the rotation axis. This means, that only the part of the vane closest to the backplate is removed, so that the part of the vane that is working most efficiently on the working fluid remains .
  • the vane shape can be modified in the area of the downstream side so that the design conforms closely to the so-called "radial element” design. This ensures that the vane stresses are kept to an acceptable low level .
  • the impeller has radially spaced and axially extended ribs projecting from the backplate on the other side of the backplate from the lines of connection with the vanes.
  • Labyrinth seals may then be provided on a casing of the impeller, the seals facing the backplate so as to mesh with the ribs .
  • the impeller may have a casing with a sealing portion which forms a seal with the radially outer peripheral surface of the backplate.
  • the inventive compressor comprises an inventive impeller, as previously described and an inventive turbocharger comprises an inventive compressor.
  • the inventive compressor and the inventive turbocharger have the same advantages as the inventive impeller has.
  • the inventive impeller can have an increased impeller creep life compared to a conventional impeller. Moreover, the necessity for coolant flow can be kept to a minimum.
  • Fig. 1 schematically shows a turbocharger in a sectional view.
  • Fig. 2 schematically shows part of a conventional turbocharger compressor impeller in a sectional view.
  • Fig. 3 schematically shows part of an embodiment of the inventive turbocharger compressor impeller in a sectional view.
  • Fig. 4 schematically shows part of an alternative embodiment of the inventive turbocharger compressor impeller in a sectional view.
  • FIG. 1 schematically shows a turbocharger in a sectional view.
  • the turbocharger comprises a turbine 11 and a compressor 10.
  • the turbine 11 and the compressor 10 are connected by a shaft 20.
  • the turbine 11 includes a rotor 4 which is located inside a turbine casing 3.
  • the turbine casing 3 has an exhaust inlet 5 which leads to the rotor 4 so that the exhaust entering the exhaust inlet 5 activates the rotor 4.
  • the turbine casing 3 has an exhaust outlet 6 through which the exhaust coming from the rotor 4 leaves the turbine casing 3.
  • the arrows 18 indicate the exhaust stream entering the turbine casing 3 through the exhaust inlet 5, activating the rotor 4 and leaving the turbine casing 3 through the exhaust outlet 6.
  • the compressor 10 includes an impeller 12 which is located inside a compressor casing 1. Moreover, the compressor 10 has an air inlet 7 which air leads to the impeller 12 and an air outlet 8 through which the air coming from the impeller 12 leaves the compressor casing 1.
  • the arrows 19 indicate the air stream entering the compressor casing 1 through the air inlet 7, being compressed by the impeller 12 and leaving the compressor casing 1 through the air outlet 8.
  • the impeller 12 comprises a backplate 2 and vanes 9.
  • the backplate 2 is connected to the shaft 20. Further, the backplate 2 is generally conical in shape and a plurality of circumferentially spaced arcuate vanes 9 are formed about its periphery. Typically the vanes are backswept.
  • the back surface 16 of the impeller 12 has radially spaced and axially extended ribs 17.
  • Labyrinth seals 13 are mounted to the compressor casing 1 opposite to the back surface 16 of the impeller 12 so as to mesh with the ribs 17. The labyrinth seals 13 engage the annular ribs 17 to reduce the leakage of compressed air towards the bearings along the back surface 16 of the impeller 12.
  • the backplate 2 comprises a radially outer peripheral surface 25.
  • a sealing portion 50 of the casing forms a seal with a radially outer peripheral surface 25 of the backplate to further reduce the leakage of compressed air.
  • the rotor 4 of the turbine 11 is connected to the shaft 20 so that the activated rotor 4 activates the shaft 20.
  • the shaft 20 is further connected to the impeller 12 inside the compressor 10. Hence, the rotor 4 activates the impeller 12 by means of the shaft 20.
  • the rotation axis is indicated by reference numeral 21.
  • the exhaust stream 18 entering the exhaust inlet 5 activates the rotor 4 and leaves the turbine through the exhaust outlet 6.
  • the arrows 18 indicate the direction of the exhaust stream.
  • the impeller 12 in the compressor 10 driven by the rotor 4 sucks atmospherically fresh air into the air inlet 7 and compresses it to precompressed fresh air, which enters the air outlet 8.
  • the compressed air is then used for example in a reciprocating engine like e.g. a diesel engine.
  • the arrows 19 indicate the air stream direction.
  • FIG 2 schematically shows part of a conventional turbocharger compressor impeller 12 in a sectional view.
  • the impeller 12 is, for example, made from aluminium.
  • the impeller 12 comprises a backplate 2 and a vane 9.
  • the vane 9 is connected to the backplate 2 at a line of connection 22.
  • Each vane 9 comprises an upstream side 14 and a downstream side 15.
  • the air which is sucked into the air inlet 7 arrives at the upstream side 14 of the vane 9, passes the vane 9 along the direction 19 and leaves it at the downstream side 15 towards the air outlet 8.
  • an outer side 23 Opposite to the line of connection 22 an outer side 23 is located.
  • the outer side 23 has a concave shape.
  • the upstream side 14 runs, perpendicular to the rotation axis 21. However, an angle may be present between the upstream side 14 and the rotation axis 21 may have a value between 0° and ⁇ 100.
  • the downstream side 15 is orientated perpendicular to a radial direction which is defined by the rotation axis 21..
  • the radially outer peripheral surface 25 is located in a plane with a normal being locally parallel to the radial direction. The distance between the radially outer peripheral surface 25 and the rotation axis 21 is indicated by reference numeral 30.
  • Figure 3 schematically shows part of an inventive turbocharger compressor impeller 112 in a sectional view. Elements which correspond to elements of figure 1 or 2 are designated with the same reference numerals and will not be described again in detail.
  • the conventional impeller 12, as it is shown in figure 2, and the inventive impeller 112, which is shown in figure 3, differ in the shape of the downstream side 15 of the vane 9 and in the radial location of the radially outer peripheral surface 25 of the backplate 2.
  • the downstream side 15 of the inventive impeller 112 comprises an edge portion 27 which is located near the outer side 23 and a connecting portion 24 which is located near the line of connection 22 and connects the line of connection 22 to the edge portion 27.
  • the connecting portion 24 in figure 3 has a convex rounded shape. However, it can also have another shape, for example a linear shape or an S-shape (although a part of the S-shape may be a convex rounded portion) .
  • the edge portion 27 which is located near the outer side 23 is further orientated perpendicular to a radial direction which is defined by the rotation axis 21. Furthermore, the edge portion 27 which is located near the outer side 23 may run parallel to the rotation axis 21. This is the case for the vane 9, which is shown in figure 3.
  • the edge portion 27 of the downstream side 15 has a length in the direction of the rotation axis 21 of more than 50% of the length of the downstream side 15 in the direction of the rotation axis 21.
  • the edge portion 27 which is located near the outer side 23 adjoins to the connecting portion 24 which is located near the line of connection 22.
  • the connecting portion 24 adjoins to the radially outer peripheral surface 25, which has the same properties as the corresponding radially outer peripheral surface 25 in figure 2.
  • the distance between the radially peripheral outer surface 25 and the rotation axis 21 in figure 3 is indicated by reference numeral 31 and is smaller than the corresponding distance 30 of the conventional impeller 12, which is shown in figure 2.
  • the vane 9 of the inventive impeller 112 projects radially over the backplate 2.
  • Figure 3 further shows a tangent 26 of the connecting portion 24 at the point, where the connecting portion 24 is adjacent to the radially outer peripheral surface 25.
  • the angle 29 between the tangent 26 and a line 28 radial to the rotation axis 21 has a value between 10° and 45°, preferably between 15° and 25°.
  • Figure 4 schematically shows part of an alternative embodiment of the inventive turbocharger compressor impeller 212 in a sectional view. Elements which correspond to elements of figure 3 are designated with the same reference numerals and are not described again in detail.
  • the impeller 212 which is shown in figure 4 comprises a connecting portion 24 with an S-shape.
  • the radially outer peripheral surface 25 in figure 4 includes an angle 32 to the rotation axis 21.
  • the angle 32 has a value between 0° and 45°, preferably between 15° and 25°. This further reduces stress and temperature on the back surface 16.
  • the connecting portion has an S-shape in the present embodiment it could as well have other shapes like, e.g., the convex rounded shape of the connecting portion of the first embodiment, or a linear shape.
  • the improved design of the inventive impeller 112, 212 reduces vane leakage losses and keeps vane stresses to an acceptable low level. This increases the impeller creep life and minimises the necessity for coolant flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An impeller (112, 212) comprising a rotation axis (21), a radial direction, a backplate (2) and a number of vanes (9) which are connected to the backplate (2) at a line of connection (22) is provided. Each vane (9) comprises an upstream side (14), a downstream side (15) and an outer side (23). The downstream side (15) of each vane (9) comprises an edge portion (27) which is located near the outer side (23). The vanes (9) project radially over the backplate (2) and the downstream side (15) further comprises a connecting portion (24) connecting the edge portion (27) to the backplate (2) and including an angle with the radial direction. The connecting portion (24) comprises a convex rounded portion which is located near the line of connection (22). Moreover, a turbocharger comprising an inventive impeller (112, 212) is disclosed.

Description

Impeller and Turbocharger
The present invention relates to an impeller and a turbocharger .
An industrial turbocharger compressor impeller is typically made from aluminium. This material is relatively cheap, is easy to machine and is light enough so that turbo lag is not a major problem. Current turbocharger impellers for medium speed diesel engines tend not to have a through bore since this minimises the stress in the impeller material and reduces the likelihood of the impeller failing due to fatigue during a typical 50,000 hour life.
The life of such an impeller tends to be governed by creep of the impeller material, so that maximum operating pressure ratios are limited to around 5 : 1 for typical industrial duties. Impeller creep failure is associated with areas of high stress and high temperature. The area of highest temperature, and consequently the area which determines the creep life, is on the back of the impeller near the outer diameter. This is an area where typically a labyrinth seal is located to reduce the leakage of compressed air towards the bearings. The high temperature is associated with windage heating in that area.
The impeller life must typically achieve 50,000 hours. This is achieved traditionally by limiting the operating speed of the turbocharger in line with calculations of the creep life. At lower operating speeds the impeller stresses are lower, the compressed air at the downstream side of the impeller is cooler, and the windage heating is less than at higher operating speed.
More recently cooled air at high pressure has been fed into the area at the back of the impeller to keep the impeller material cool . In US 5,297,928 and US 6,190,123 Bl methods for direct cooling the rear wall of a compressor impeller are disclosed, wherein a gaseous cooling medium is directed onto the rear wall.
In US 6,257,834 Bl a method for indirect cooling of the flow in radial gaps formed between rotors and stators of turbo machines is provided. The method includes the step of using water as a cooling fluid for stator part adjacent to the radial gap.
In WO 01/29425 Al a combination of direct and indirect cooling of the flow in radial gaps formed between rotors and stators of turbine-type machines is disclosed, wherein a first cooling fluid, preferably water, is used for indirect cooling and a second gaseous cooling fluid, preferably air, is used for direct cooling.
The cooled air is typically taken from the diesel engine air manifold, after the compressed air has been cooled by the charge air cooler. The introduction of this cooled air is a parasitic loss on the turbocharger efficiency, since the turbocharger has to compress the coolant air but the air is not used in the diesel engine. Also this cooled air leaks into the main stream of the compressor flow between impeller and diffuser and will cause a disturbance to the flow which reduces the compressor efficiency. Nevertheless, by cooling the impeller the compressor is allowed to operate at higher speed while still achieving the required 50,000 hours life.
Typically, by cooling the impeller by 200C, an additional 0.2 bar of boost pressure can be achieved with this system and this typically allows the engine rate power to increase by around 5%.
As well as the parasitic loss in adding this high pressure coolant air, the pressure behind the impeller increases and the thrust load, and consequently parasitic thrust bearing losses, increase.
It is a first objective of the present invention to provide an advantageous impeller, a second objective to provide an advantageous compressor and a third objective to provide an advantageous turbocharger .
The first objective may be solved by an impeller as claimed in claim 1. The second objective may be solved by a compressor as claimed in claim 11. The third objective may be solved by a turbocharger as claimed in claim 12. The depending claims define further developments of the invention.
An inventive impeller comprises a rotation axis, a radial direction, a backplate and a number of vanes which are connected to the backplate at a line of connection. Each vane comprises an upstream side, a downstream side and an outer side. The downstream side of each vane comprises an edge portion which is located near the outer side. The vanes project radially over the backplate and the downstream side further comprises a connecting portion connecting the edge portion to the line of connection between the respective vane and the backplate and including an angle with the radial direction. This means, that part of the inventive impeller's downstream side is removed compared to a conventional impeller's downstream side. The removed area is at high diameter so that stresses are reduced in that area. Also this is the hottest area of the impeller so that the temperature of the impeller is also reduced. However, the radial projection of the vanes means that radially outer parts of the vanes are preserved, which helps to maintain the ability of the impeller to pressurise the flow.
The edge portion may be orientated perpendicular to the radial direction. The connecting portion may have a convex rounded portion which is located near the connection line. For example, in some embodiments such a convex rounded portion can extend from the edge portion to the line of connection between the respective vane and the backplate. In other embodiments, such a convex rounded portion can be part of an S-shape portion which may extend from the edge portion to the line of connection between the respective vane and the backplate.
Preferably, each vane is backswept on moving in an airflow direction from its upstream side to its downstream side. Backsweeping the vanes can introduce an extra tangential component into the flow leaving the impeller, which can improve flow stability and efficiency. Backsweep can also increase bending stresses in the vanes, but advantageously these stresses can be reduced by employing a connecting portion which has a convex rounded portion located near the connection line.
A further advantage of employing a connecting portion which has a convex rounded portion located near the connection line is that the high centrifugal stresses which can be generated in the region where the vane and the backplate meet can be reduced. Particularly advantageous in this respect is a connecting portion which has an S-shape portion.
Moreover, the backplate can comprise a radially outer peripheral surface and the connecting portion can be adjacent to the radially outer peripheral surface of the backplate. The radially outer peripheral surface of the backplate may be located in a plane with a normal being locally parallel to the radial direction. This means, that the radially outer surface may run parallel to the rotation axis. Alternatively, the radially outer peripheral surface of the backplate can be located in a plane with a normal which includes an angle between 0° and 45° with the radial direction. Preferably, the angle may have a value between 15° and 25°. This further reduces stress and temperature on the surface of the backplate .
The radially outer surface of the inventive impeller may especially be located at a radial position closer to the rotation axis than the radially outer surface of a conventional impeller. In other words, the distance between the radially outer surface and the rotation axis of an inventive impeller is smaller than the distance between the radially outer surface and the rotation axis of a conventional impeller. By removing some of the backplate of the impeller, the aerodynamic performance of the impeller could be reduced. This reduction is associated with leakage around the base of the vanes, which would otherwise be prevented by the presence of the backplate, and a reduction in the diameter of the impeller vanes. Moreover, a removal of part of the backplate could also increase local stresses in the impeller vanes since they will no longer be entirely supported along their entire length.
To reduce the potential aerodynamic losses and local vane stress the shape of the vane at the impeller tip is preferably carefully chosen: An angle between a tangent located at the connecting portion adjacent to the connection line and the radial direction may have a value between 10° and 45°, preferably between 15° and 25°. This reduces vane leakage losses. Moreover, the edge portion of the downstream side can have a length in the direction of the rotation axis of more than 50% of the length of the downstream side in the direction of the rotation axis. This means, that only the part of the vane closest to the backplate is removed, so that the part of the vane that is working most efficiently on the working fluid remains .
The vane shape can be modified in the area of the downstream side so that the design conforms closely to the so-called "radial element" design. This ensures that the vane stresses are kept to an acceptable low level .
Typically, the impeller has radially spaced and axially extended ribs projecting from the backplate on the other side of the backplate from the lines of connection with the vanes. Labyrinth seals may then be provided on a casing of the impeller, the seals facing the backplate so as to mesh with the ribs .
Additionally or alternatively, the impeller may have a casing with a sealing portion which forms a seal with the radially outer peripheral surface of the backplate.
The inventive compressor comprises an inventive impeller, as previously described and an inventive turbocharger comprises an inventive compressor. The inventive compressor and the inventive turbocharger have the same advantages as the inventive impeller has.
The inventive impeller can have an increased impeller creep life compared to a conventional impeller. Moreover, the necessity for coolant flow can be kept to a minimum.
Further features, properties, and advantages of the present invention will become clear from the following description of an embodiment in conjunction with the accompanying drawings. Each features or a combination of features can be advantageous .
Fig. 1 schematically shows a turbocharger in a sectional view.
Fig. 2 schematically shows part of a conventional turbocharger compressor impeller in a sectional view.
Fig. 3 schematically shows part of an embodiment of the inventive turbocharger compressor impeller in a sectional view. Fig. 4 schematically shows part of an alternative embodiment of the inventive turbocharger compressor impeller in a sectional view.
In the following a first embodiment of the inventive impeller and the inventive turbocharger will be described with reference to Figures 1 to 4. Figure 1 schematically shows a turbocharger in a sectional view. The turbocharger comprises a turbine 11 and a compressor 10. The turbine 11 and the compressor 10 are connected by a shaft 20.
The turbine 11 includes a rotor 4 which is located inside a turbine casing 3. The turbine casing 3 has an exhaust inlet 5 which leads to the rotor 4 so that the exhaust entering the exhaust inlet 5 activates the rotor 4. Further the turbine casing 3 has an exhaust outlet 6 through which the exhaust coming from the rotor 4 leaves the turbine casing 3. The arrows 18 indicate the exhaust stream entering the turbine casing 3 through the exhaust inlet 5, activating the rotor 4 and leaving the turbine casing 3 through the exhaust outlet 6.
The compressor 10 includes an impeller 12 which is located inside a compressor casing 1. Moreover, the compressor 10 has an air inlet 7 which air leads to the impeller 12 and an air outlet 8 through which the air coming from the impeller 12 leaves the compressor casing 1. The arrows 19 indicate the air stream entering the compressor casing 1 through the air inlet 7, being compressed by the impeller 12 and leaving the compressor casing 1 through the air outlet 8.
The impeller 12 comprises a backplate 2 and vanes 9. The backplate 2 is connected to the shaft 20. Further, the backplate 2 is generally conical in shape and a plurality of circumferentially spaced arcuate vanes 9 are formed about its periphery. Typically the vanes are backswept. The back surface 16 of the impeller 12 has radially spaced and axially extended ribs 17. Labyrinth seals 13 are mounted to the compressor casing 1 opposite to the back surface 16 of the impeller 12 so as to mesh with the ribs 17. The labyrinth seals 13 engage the annular ribs 17 to reduce the leakage of compressed air towards the bearings along the back surface 16 of the impeller 12.
Moreover, the backplate 2 comprises a radially outer peripheral surface 25. A sealing portion 50 of the casing forms a seal with a radially outer peripheral surface 25 of the backplate to further reduce the leakage of compressed air.
The rotor 4 of the turbine 11 is connected to the shaft 20 so that the activated rotor 4 activates the shaft 20. The shaft 20 is further connected to the impeller 12 inside the compressor 10. Hence, the rotor 4 activates the impeller 12 by means of the shaft 20. The rotation axis is indicated by reference numeral 21.
In the turbine 11 the exhaust stream 18 entering the exhaust inlet 5 activates the rotor 4 and leaves the turbine through the exhaust outlet 6. The arrows 18 indicate the direction of the exhaust stream. Meanwhile, the impeller 12 in the compressor 10 driven by the rotor 4 sucks atmospherically fresh air into the air inlet 7 and compresses it to precompressed fresh air, which enters the air outlet 8. The compressed air is then used for example in a reciprocating engine like e.g. a diesel engine. The arrows 19 indicate the air stream direction.
Figure 2 schematically shows part of a conventional turbocharger compressor impeller 12 in a sectional view. The impeller 12 is, for example, made from aluminium. The impeller 12 comprises a backplate 2 and a vane 9. The vane 9 is connected to the backplate 2 at a line of connection 22. Each vane 9 comprises an upstream side 14 and a downstream side 15. The air which is sucked into the air inlet 7 arrives at the upstream side 14 of the vane 9, passes the vane 9 along the direction 19 and leaves it at the downstream side 15 towards the air outlet 8.
Opposite to the line of connection 22 an outer side 23 is located. The outer side 23 has a concave shape. The upstream side 14 runs, perpendicular to the rotation axis 21. However, an angle may be present between the upstream side 14 and the rotation axis 21 may have a value between 0° and ±100. The downstream side 15 is orientated perpendicular to a radial direction which is defined by the rotation axis 21.. The radially outer peripheral surface 25 is located in a plane with a normal being locally parallel to the radial direction. The distance between the radially outer peripheral surface 25 and the rotation axis 21 is indicated by reference numeral 30.
Figure 3 schematically shows part of an inventive turbocharger compressor impeller 112 in a sectional view. Elements which correspond to elements of figure 1 or 2 are designated with the same reference numerals and will not be described again in detail. The conventional impeller 12, as it is shown in figure 2, and the inventive impeller 112, which is shown in figure 3, differ in the shape of the downstream side 15 of the vane 9 and in the radial location of the radially outer peripheral surface 25 of the backplate 2.
The downstream side 15 of the inventive impeller 112 comprises an edge portion 27 which is located near the outer side 23 and a connecting portion 24 which is located near the line of connection 22 and connects the line of connection 22 to the edge portion 27. The connecting portion 24 in figure 3 has a convex rounded shape. However, it can also have another shape, for example a linear shape or an S-shape (although a part of the S-shape may be a convex rounded portion) . The edge portion 27 which is located near the outer side 23 is further orientated perpendicular to a radial direction which is defined by the rotation axis 21. Furthermore, the edge portion 27 which is located near the outer side 23 may run parallel to the rotation axis 21. This is the case for the vane 9, which is shown in figure 3. The edge portion 27 of the downstream side 15 has a length in the direction of the rotation axis 21 of more than 50% of the length of the downstream side 15 in the direction of the rotation axis 21.
The edge portion 27 which is located near the outer side 23 adjoins to the connecting portion 24 which is located near the line of connection 22. At the line of connection 22 the connecting portion 24 adjoins to the radially outer peripheral surface 25, which has the same properties as the corresponding radially outer peripheral surface 25 in figure 2. The distance between the radially peripheral outer surface 25 and the rotation axis 21 in figure 3 is indicated by reference numeral 31 and is smaller than the corresponding distance 30 of the conventional impeller 12, which is shown in figure 2. Moreover, the vane 9 of the inventive impeller 112 projects radially over the backplate 2.
Figure 3 further shows a tangent 26 of the connecting portion 24 at the point, where the connecting portion 24 is adjacent to the radially outer peripheral surface 25. The angle 29 between the tangent 26 and a line 28 radial to the rotation axis 21 has a value between 10° and 45°, preferably between 15° and 25°.
Figure 4 schematically shows part of an alternative embodiment of the inventive turbocharger compressor impeller 212 in a sectional view. Elements which correspond to elements of figure 3 are designated with the same reference numerals and are not described again in detail. Unlike figure 3, the impeller 212 which is shown in figure 4 comprises a connecting portion 24 with an S-shape. Moreover, the radially outer peripheral surface 25 in figure 4 includes an angle 32 to the rotation axis 21. The angle 32 has a value between 0° and 45°, preferably between 15° and 25°. This further reduces stress and temperature on the back surface 16. Although the connecting portion has an S-shape in the present embodiment it could as well have other shapes like, e.g., the convex rounded shape of the connecting portion of the first embodiment, or a linear shape.
The improved design of the inventive impeller 112, 212 reduces vane leakage losses and keeps vane stresses to an acceptable low level. This increases the impeller creep life and minimises the necessity for coolant flow.

Claims

Claims
1. An impeller (112, 212) comprising a rotation axis (21), a radial direction, a backplate (2) and a number of vanes (9) which are connected to the backplate (2) at a line of connection (22), each vane (9) comprising an upstream side (14), a downstream side (15) and an outer side (23), the downstream side (15) of each vane (9) comprising an edge portion (27) which is located near the outer side (23), wherein the vanes (9) project radially over the backplate (2) and the downstream side (15) further comprises a connecting portion (24) connecting the edge portion (27) to the line of connection (22) and including an angle with the radial direction, characterised in that the connecting portion (24) comprises a convex rounded portion which is located near the line of connection (22) .
2. The impeller (112, 212) as claimed in claim 1, characterised in that the edge portion (27) is orientated perpendicular to the radial direction.
3. The impeller (112, 212) as claimed in claim 1 or 2, characterised in that each vane is backswept on moving in an airflow direction from its upstream side to its downstream side .
4. The impeller (112, 212) as claimed in any of the claims 1 to 3, characterised in that the backplate (2) comprises a radially outer peripheral surface (25) and the connecting portion (24) is adjacent to the radially outer peripheral surface (25) of the backplate (2) .
5. The impeller (112, 212) as claimed in claim 4, characterised in that the radially outer peripheral surface
(25) of the backplate (2) is located in a plane with a normal being locally parallel to the radial direction.
6. The impeller (112, 212) as claimed in claim 4, characterised in that the radially outer peripheral surface (25) of the backplate (2) is located in a plane with a normal which includes an angle (32) between 0° and 45° with the radial direction.
7. The impeller (112, 212) as claimed in claim 6, characterised in that the angle (32) has a value between 15° and 25°.
8. The impeller (112, 212) as claimed in any of the claims 1 to 7, characterised in that an angle (29) between the radial direction and a tangent (26) of the connecting portion (24) adjacent to the line of connection (22) has a value between 10° and 45°.
9. The impeller (112, 212) as claimed in claim 8, characterised in that the angle (29) has a value between 15° and 25°.
10. The impeller (112, 212) as claimed in any of the claims 1 to 9, characterised in that the edge portion (27) of the downstream side (15) has a length in the direction of the rotation axis (21) of more than 50% of the length of the downstream side (15) in the direction of the rotation axis (21) .
11. A compressor comprising an impeller (112, 212) as claimed in any of the claims 1 to 10.
12. A turbocharger comprising a compressor as claimed in claim 11.
EP08872443.0A 2008-02-14 2008-12-18 Impeller and turbocharger Not-in-force EP2252798B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08872443.0A EP2252798B1 (en) 2008-02-14 2008-12-18 Impeller and turbocharger

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08002766A EP2090788A1 (en) 2008-02-14 2008-02-14 Impeller and turbocharger
PCT/GB2008/004190 WO2009101376A1 (en) 2008-02-14 2008-12-18 Impeller and turbocharger
EP08872443.0A EP2252798B1 (en) 2008-02-14 2008-12-18 Impeller and turbocharger

Publications (2)

Publication Number Publication Date
EP2252798A1 true EP2252798A1 (en) 2010-11-24
EP2252798B1 EP2252798B1 (en) 2018-09-05

Family

ID=39597663

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08002766A Withdrawn EP2090788A1 (en) 2008-02-14 2008-02-14 Impeller and turbocharger
EP08872443.0A Not-in-force EP2252798B1 (en) 2008-02-14 2008-12-18 Impeller and turbocharger

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08002766A Withdrawn EP2090788A1 (en) 2008-02-14 2008-02-14 Impeller and turbocharger

Country Status (6)

Country Link
US (1) US20100322781A1 (en)
EP (2) EP2090788A1 (en)
JP (1) JP5538240B2 (en)
KR (1) KR20100121515A (en)
CN (1) CN101952603B (en)
WO (1) WO2009101376A1 (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2975733B1 (en) * 2011-05-23 2015-12-18 Turbomeca CENTRIFUGAL COMPRESSOR WHEEL
DE102011051650B4 (en) * 2011-07-07 2020-04-30 Atlas Copco Energas Gmbh Turbo machine
JP5967966B2 (en) * 2012-02-13 2016-08-10 三菱重工コンプレッサ株式会社 Impeller and rotating machine equipped with the same
CN104246167B (en) * 2012-05-03 2018-02-06 博格华纳公司 Reduce the super backboard impeller of stress
CN102691527B (en) * 2012-06-12 2014-06-04 中国科学院工程热物理研究所 Groove structure on back of open centripetal turbine blade
CN103775198B (en) * 2014-02-26 2016-05-18 岑溪市东正新泵业贸易有限公司 Rotary impeller booster
JP6559401B2 (en) * 2014-03-31 2019-08-14 株式会社Ihi Compressor impeller, centrifugal compressor, and supercharger
US9845810B2 (en) * 2014-06-24 2017-12-19 Concepts Nrec, Llc Flow control structures for turbomachines and methods of designing the same
DE102014218663A1 (en) * 2014-09-17 2016-03-17 Siemens Aktiengesellschaft Radial turbo fluid energy machine
DE102014219107A1 (en) * 2014-09-23 2016-03-24 Siemens Aktiengesellschaft Radial compressor impeller and associated centrifugal compressor
CN104314863A (en) * 2014-10-29 2015-01-28 湖南天雁机械有限责任公司 Gas compressor impeller with function of reducing axial load
CN104373376A (en) * 2014-10-29 2015-02-25 湖南天雁机械有限责任公司 Arc-shaped oblique flow turbocharger compressor impeller
CN104314864A (en) * 2014-10-29 2015-01-28 湖南天雁机械有限责任公司 Gas compressor oblique flow impeller with function of reducing axial load of turbocharger
DE102014224283A1 (en) * 2014-11-27 2016-06-02 Robert Bosch Gmbh Compressor with a sealing channel
CN104500440A (en) * 2014-12-12 2015-04-08 常州环能涡轮动力股份有限公司 Low-cycle-fatigue-resistant turbocharger air compressor impeller
US9856886B2 (en) * 2015-01-08 2018-01-02 Honeywell International Inc. Multistage radial compressor baffle
US11015250B2 (en) * 2015-03-17 2021-05-25 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Impeller for rotary machine, compressor, supercharger, and method for producing impeller for rotary machine
KR102061517B1 (en) * 2016-09-01 2020-02-11 삼성전자주식회사 Cleaner
CN109306967A (en) * 2017-07-28 2019-02-05 深圳市美好创亿医疗科技有限公司 Blower
US11041405B2 (en) 2019-09-18 2021-06-22 Garrett Transportation I Inc. Turbocharger turbine wheel
JP7438240B2 (en) * 2019-12-09 2024-02-26 三菱重工エンジン＆ターボチャージャ株式会社 Centrifugal compressor impeller, centrifugal compressor and turbocharger
WO2021192019A1 (en) * 2020-03-24 2021-09-30 三菱重工エンジン＆ターボチャージャ株式会社 Impeller of centrifugal compressor, centrifugal compressor provided with impeller, and method for manufacturing impeller
WO2022029932A1 (en) * 2020-08-05 2022-02-10 三菱重工エンジン＆ターボチャージャ株式会社 Impeller for centrifugal compressor, and centrifugal compressor
CN112443359B (en) * 2020-11-20 2022-12-27 蜂巢蔚领动力科技(江苏)有限公司 Centripetal turbine impeller with S-shaped meridian surface outlet edge
US11702937B2 (en) 2021-04-20 2023-07-18 Saudi Arabian Oil Company Integrated power pump

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1796057A (en) * 1928-03-17 1931-03-10 Smith Frederick Robertson Supercharging fan for internal-combustion engines
GB347043A (en) * 1929-06-07 1931-04-23 Lucie Annie Jeanne Rateau Improvements in or relating to the blades of radial rotors of centrifugal blowers and compressors
JPS4719804U (en) * 1971-01-14 1972-11-06
DE2338718A1 (en) * 1973-07-31 1975-02-13 Motoren Turbinen Union Rotor for radial turbo compressor - from which several flows are derived, has blades with stepped ends
JPS50134705U (en) * 1974-04-22 1975-11-06
JPS52112507U (en) * 1976-02-24 1977-08-26
JPS60188887U (en) * 1984-05-25 1985-12-14 新明和工業株式会社 Impeller for vortex pump
US5297928A (en) 1992-06-15 1994-03-29 Mitsubishi Jukogyo Kabushiki Kaisha Centrifugal compressor
DE4318580A1 (en) * 1993-06-04 1994-12-08 Sel Alcatel Ag Radial fan
DE4431840A1 (en) * 1994-09-07 1996-03-14 Behr Gmbh & Co Fan for car cooling system with radial impeller
CN2213877Y (en) * 1994-09-24 1995-11-29 孙敏超 Back bend impeller
DE19845375A1 (en) 1998-10-02 2000-04-06 Asea Brown Boveri Indirect cooling process for flow in gap between turbine rotor and stator, involving use of water to cool stator part adjacent to gap
EP0961033B1 (en) 1998-05-25 2003-10-08 ABB Turbo Systems AG Radial compressor
EP1222399B1 (en) 1999-10-20 2003-08-13 ABB Turbo Systems AG Method and device for cooling the flow in the radial gaps formed between rotors and stators of turbine-type machines
US6663347B2 (en) * 2001-06-06 2003-12-16 Borgwarner, Inc. Cast titanium compressor wheel

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009101376A1 *

Also Published As

Publication number Publication date
JP5538240B2 (en) 2014-07-02
US20100322781A1 (en) 2010-12-23
EP2252798B1 (en) 2018-09-05
CN101952603B (en) 2013-06-26
WO2009101376A1 (en) 2009-08-20
KR20100121515A (en) 2010-11-17
EP2090788A1 (en) 2009-08-19
CN101952603A (en) 2011-01-19
JP2011512479A (en) 2011-04-21

Similar Documents

Publication Publication Date Title
EP2252798B1 (en) Impeller and turbocharger
EP1092085B1 (en) Low speed high pressure ratio turbocharger
US8186938B2 (en) Turbine apparatus
CA2496543C (en) Recirculation structure for a turbocompressor
EP1926915B1 (en) Stationary seal ring for a centrifugal compressor
EP1937979B1 (en) Centrifugal compressor including a seal system
EP3043073B1 (en) Multistage radial compressor baffle
EP2930370A1 (en) Centrifugal compressor, supercharger with same, and method for operating centrifugal compressor
US20140064937A1 (en) Fan blade brush tip
US8480351B2 (en) Compressor unit
JP5230590B2 (en) Exhaust inlet casing of exhaust turbine supercharger
CN110344927B (en) Internal combustion engine
WO2018002618A1 (en) Centrifugal compressor with diffuser with throat
JP5497012B2 (en) Compressor cover for a turbine engine having an axial abutment
US11879389B2 (en) Concentric introduction of the waste-gate mass flow into a flow-optimized axial diffusor
RU2809677C1 (en) Improved turbine and blade to protect blade root from hot gases from flow channel
JP2008208734A (en) Two-stage compression type exhaust turbine supercharger
JP2013119801A (en) Supercharger

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20100902

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20170726

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20180509

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK 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: 1038143

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180915

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602008056880

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180905

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

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: 20181205

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: 20181205

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: 20180905

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: 20180905

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: 20180905

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: 20181206

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1038143

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180905

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

Ref country code: ES

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

Effective date: 20180905

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: 20180905

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: 20180905

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

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: 20180905

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: 20180905

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: 20180905

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: 20180905

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: 20180905

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: 20190105

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: 20180905

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: 20180905

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

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: 20180905

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: 20190105

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602008056880

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602008056880

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

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

Ref country code: DK

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

Effective date: 20180905

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

26N No opposition filed

Effective date: 20190606

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20181218

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: 20180905

Ref country code: LU

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

Effective date: 20181218

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: 20180905

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20181231

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

Ref country code: DE

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

Effective date: 20190702

Ref country code: FR

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

Effective date: 20181231

Ref country code: IE

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

Effective date: 20181218

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: 20181231

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

Ref country code: CH

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

Effective date: 20181231

Ref country code: LI

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

Effective date: 20181231

Ref country code: GB

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

Effective date: 20181218

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

Ref country code: MT

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

Effective date: 20181218

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

Ref country code: TR

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

Effective date: 20180905

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: 20180905

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: 20081218