WO2009043659A2 - A turbomachine - Google Patents

A turbomachine Download PDF

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Publication number
WO2009043659A2
WO2009043659A2 PCT/EP2008/061508 EP2008061508W WO2009043659A2 WO 2009043659 A2 WO2009043659 A2 WO 2009043659A2 EP 2008061508 W EP2008061508 W EP 2008061508W WO 2009043659 A2 WO2009043659 A2 WO 2009043659A2
Authority
WO
WIPO (PCT)
Prior art keywords
turbomachine
turbulator
rotor
turbulators
cylinder
Prior art date
Application number
PCT/EP2008/061508
Other languages
French (fr)
Other versions
WO2009043659A3 (en
Inventor
John David Maltson
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP08803486A priority Critical patent/EP2193256B1/en
Priority to US12/680,791 priority patent/US8016555B2/en
Priority to AT08803486T priority patent/ATE509187T1/en
Publication of WO2009043659A2 publication Critical patent/WO2009043659A2/en
Publication of WO2009043659A3 publication Critical patent/WO2009043659A3/en

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
    • F01D5/12—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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • This invention relates to cooling of a turbomachine particularly but not exclusively in the field of a gas turbine where a slip ring arrangement is utilised to obtain data from sensors in the engine.
  • the present invention arose in an attempt to reduce heat transfer between components and to reduce the temperature of components in a turbomachine.
  • a turbomachine comprising a stator, a rotor, and blade discs mounted on the rotor, the rotor being mounted for rotation about an axis, the rotation being relative to the stator, wherein the rotor includes a turbulator cylinder on the curved external surface of which is provided a plurality of turbulators, wherein the stator includes an annular shroud that extends around the turbulator cylinder, the turbulator cylinder and the annular shroud both being concentric with the axis of rotation of the rotor, a clearance being defined between adjacent opposed curved surfaces of the turbulator cylinder and annular shroud, wherein the plurality of turbulators provided on the curved external surface of the turbulator cylinder increase heat transfer to a coolant flowing between the adjacent opposed curved surfaces of the turbulator cylinder and annular shroud.
  • the turbulators increase a temperature gradient along the axis of the rotor and this gradient may be arranged to reduce the effect of heat on particular components which in the case of the specific embodiment are sensitive instrumentation components .
  • the turbulators may take a number of forms, for example, pips or surface indentations.
  • the preferred form of the turbulators is a longitudinal rib. These may be provided at various angles relative to the axis of rotation of the rotor but in the preferred described embodiment the ribs are substantially parallel to the axis of rotation.
  • the turbulators may be milled into the surface of the turbulator cylinder or added to the surface and fixed thereto by welding.
  • the longitudinal rib height is preferably less than 0.3 times the clearance between the adjacent opposed curved surfaces of the turbulator cylinder and annular shroud. Preferably, the rib height is greater than 0.05 times the clearance.
  • the rib height is given substantially by the relationship of rib pitch divided by a factor in this case ten .
  • Figure 1 shows in simplified form a turbomachine in accordance with the invention
  • Figure 2 shows a partial section through one end of the turbomachine of figure 1 showing a cooling arrangement in accordance with the invention, as well as a slip ring arrangement for sensor wires
  • Figure 3 shows a turbulator cylinder used in the turbomachine shown in figure 2 with figure 3a being a section along the axis of the rotor, figure 3b being an end view of the turbulator cylinder showing its relationship to a stator and figure 3c being an enlargement of region dd of the end view of figure 3b showing a detail of turbulator ribs on the turbulator cylinder; and
  • Figure 4 is an explanatory drawing showing the effect of the turbulator ribs on a fluid flow.
  • a turbomachine 1 is provided with an axial extending rotor 2 carrying blade discs 3 providing a compressor and turbine part.
  • the rotor includes a tie bar 4 which extends into a downstream slip ring enclosure 5.
  • the slip ring enclosure provides electrical connection between sensors with the turbomachine 1 and a set of instruments 6 by means of electrical cables 7.
  • the slip ring enclosure 5 is shown in greater detail in figure 2. It comprises a generally truncated conical shaped shell having disposed to the lower side wall a cable and coolant duct 8 of generally cylindrical configuration which opens into the enclosure. An end plate 9 is provided bolted to the base apex of the conical shell. The inside of the walls of the enclosure are provided with an insulating material 10.
  • the enclosure 5 houses and protects a slip ring arrangement 12 which passes electrical signals to the cables 7 from a set of sensor wires 13 which pass into the turbomachine 1 and hence to sensors (not shown) distributed to sense parameters in the turbomachine 1.
  • the sensed parameters can include temperature, for example.
  • the rotor 2 of the turbomachine protrudes into the enclosure 5. It comprises a balance piston 14 connected to the tie bar 4 by a tie bar nut 15.
  • the balance piston 14 has bolted to it a turbulator cylinder 16.
  • the turbulator cylinder 16 connects to a quill shaft 17 through which the sensor wires 13 are routed to the slip ring arrangement 12. It is important to note that these components are part of the rotor and rotate about the axis of rotation 18.
  • the turbulator cylinder 16 is generally cylindrical in configuration but includes an inner cone 16a which reduces in diameter left to right and provides an apex at the quill shaft 17. This creates a void 16b which reduces heat transfer through metal to metal contact and also by radiation as the cone 16a acts as a heat-shield.
  • the cone 16a is spaced apart from the tie bar 4 and nut 15 and encloses it to further reduce heat transfer via conduction. It will be appreciated that some embodiments may not require this heat shield.
  • the rotor moves relative to a stator.
  • a stator This comprises a number of components which will be familiar to the person skilled in the art but in figure 2 there are shown an end plate 19 in the form of an annulus with the rotor 2 protruding through the central hole into the enclosure 5.
  • a labyrinth seal 20 is provided to prevent hot gases escaping into the enclosure cavity.
  • the end plate 19 is also insulated to prevent heat transmission.
  • the stator also includes a series of support spokes 21 two of which can be seen. These are fixed towards the radially outerwards part of the end plate 19 and are inclined inwards in a direction towards the axis of rotation 18.
  • the radially inner ends of the spokes 21 are bolted to an annular shroud 22.
  • This is provided with a central portion which is generally cylindrical which extends in a direction substantially parallel to the axis 18. This part of the arrangement is shown in greater detail in figure 3.
  • the turbulator cylinder 16 is provided with a plurality of turbulators in the form of ribs 16c milled into its surface. These extend in a parallel direction to the axis.
  • Figure 3b shows that the ribs 16c extend in a radial direction when examined end on from one side. There is a separation 16d between the ribs 16c.
  • Two adjacent ribs are shown enlarged in figure 3c. It can be seen that they are generally rectangular in cross-section and project radially out of the surface on the turbulator cylinder 16. It will be seen that their outermost corner edges are radiused. This is preferred to enhance the coolant flow although other edge profiles may be used.
  • the preferred rib profile has rib height H from the surface of turbulator cylinder 16 to the radially outermost surface of the rib, a rib spacing or pitch given by the dimension P between the rib centre lines, a rib width of W and there is a clearance to the stator of C where in this case H is given by C/4 and the pitch to height ratio is 10.
  • the pitch P is 5mm
  • the height H is 0.55 to 0.75mm
  • the rib width W is 0.5 to 0.75mm
  • the clearance C is 1.6mm
  • the rib edges have a radius of 0.10 to 0.15mm.
  • the dimensions for the rib and pitch are chosen to facilitate efficient disturbance to the fluid flow and recombination of the flow to give enhanced cooling. This will now be described with reference to figure 4.
  • the fluid flow is depicted by a simple line but the fluid flow is reality more complex than that depicted. However, as the fluid flow passes over the first rib 16c 1 it separates and turbulates over a separation region X and then reattaches over a region Y before flowing over the next rib 16c 2 . Maximum cooling is effected over the re-attachment region Y.
  • the chosen ratios of dimensions maximise the efficiency of this process.
  • the sensor signals are passed out of the turbomachine by a slip ring arrangement. It will be appreciated that other non contact methods may be used such as telemeters using wireless methods or memory devices to store the data until downloaded during service of the turbomachine.
  • the ribs extend in a direction parallel to the axis of rotation. In alternative embodiments they may be arranged at any angle which may assist in promoting a coolant flow.
  • the turbulators may be placed on the annular shroud in addition to the turbulator cylinder. These may be arranged at opposing angles to further enhance the coolant effect.

Landscapes

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

Abstract

In a first aspect the turbomachine includes a turbulator arrangement to increase the efficiency of a coolant flow between a rotor (4, 14, and 16) and a stator (22) of the turbomachine. Another aspect provides a heat shield (17) between the rotor and the stator. These features reduce or alleviate heat transfer from hot parts to parts of the turbomachine that should be maintained at a lower temperature.

Description

A Turbomachine
This invention relates to cooling of a turbomachine particularly but not exclusively in the field of a gas turbine where a slip ring arrangement is utilised to obtain data from sensors in the engine.
Gas turbines run at very high temperatures and it is important to reduce heat transfer from the high temperature parts to sensitive components such as electronic instrumentation. Slip rings are provided on a shaft of the turbine to couple sensor outputs out of the engine via suitable cables. It is desirable that engine instrumentation using the sensor outputs is not exposed to the very high temperatures present in an operating engine.
The present invention arose in an attempt to reduce heat transfer between components and to reduce the temperature of components in a turbomachine.
According to the present invention there is provided a turbomachine comprising a stator, a rotor, and blade discs mounted on the rotor, the rotor being mounted for rotation about an axis, the rotation being relative to the stator, wherein the rotor includes a turbulator cylinder on the curved external surface of which is provided a plurality of turbulators, wherein the stator includes an annular shroud that extends around the turbulator cylinder, the turbulator cylinder and the annular shroud both being concentric with the axis of rotation of the rotor, a clearance being defined between adjacent opposed curved surfaces of the turbulator cylinder and annular shroud, wherein the plurality of turbulators provided on the curved external surface of the turbulator cylinder increase heat transfer to a coolant flowing between the adjacent opposed curved surfaces of the turbulator cylinder and annular shroud.
The turbulators increase a temperature gradient along the axis of the rotor and this gradient may be arranged to reduce the effect of heat on particular components which in the case of the specific embodiment are sensitive instrumentation components .
The turbulators may take a number of forms, for example, pips or surface indentations. The preferred form of the turbulators is a longitudinal rib. These may be provided at various angles relative to the axis of rotation of the rotor but in the preferred described embodiment the ribs are substantially parallel to the axis of rotation.
The turbulators may be milled into the surface of the turbulator cylinder or added to the surface and fixed thereto by welding.
The longitudinal rib height is preferably less than 0.3 times the clearance between the adjacent opposed curved surfaces of the turbulator cylinder and annular shroud. Preferably, the rib height is greater than 0.05 times the clearance.
Preferably, the rib height is given substantially by the relationship of rib pitch divided by a factor in this case ten .
A specific embodiment of the invention will now be described with reference to the drawings in which: Figure 1 shows in simplified form a turbomachine in accordance with the invention; Figure 2 shows a partial section through one end of the turbomachine of figure 1 showing a cooling arrangement in accordance with the invention, as well as a slip ring arrangement for sensor wires; Figure 3 shows a turbulator cylinder used in the turbomachine shown in figure 2 with figure 3a being a section along the axis of the rotor, figure 3b being an end view of the turbulator cylinder showing its relationship to a stator and figure 3c being an enlargement of region dd of the end view of figure 3b showing a detail of turbulator ribs on the turbulator cylinder; and
Figure 4 is an explanatory drawing showing the effect of the turbulator ribs on a fluid flow.
As is shown in figure 1, a turbomachine 1 is provided with an axial extending rotor 2 carrying blade discs 3 providing a compressor and turbine part. The rotor includes a tie bar 4 which extends into a downstream slip ring enclosure 5. The slip ring enclosure provides electrical connection between sensors with the turbomachine 1 and a set of instruments 6 by means of electrical cables 7.
The slip ring enclosure 5 is shown in greater detail in figure 2. It comprises a generally truncated conical shaped shell having disposed to the lower side wall a cable and coolant duct 8 of generally cylindrical configuration which opens into the enclosure. An end plate 9 is provided bolted to the base apex of the conical shell. The inside of the walls of the enclosure are provided with an insulating material 10.
The enclosure 5 houses and protects a slip ring arrangement 12 which passes electrical signals to the cables 7 from a set of sensor wires 13 which pass into the turbomachine 1 and hence to sensors (not shown) distributed to sense parameters in the turbomachine 1. The sensed parameters can include temperature, for example.
The rotor 2 of the turbomachine protrudes into the enclosure 5. It comprises a balance piston 14 connected to the tie bar 4 by a tie bar nut 15. The balance piston 14 has bolted to it a turbulator cylinder 16. The turbulator cylinder 16 connects to a quill shaft 17 through which the sensor wires 13 are routed to the slip ring arrangement 12. It is important to note that these components are part of the rotor and rotate about the axis of rotation 18.
The turbulator cylinder 16 is generally cylindrical in configuration but includes an inner cone 16a which reduces in diameter left to right and provides an apex at the quill shaft 17. This creates a void 16b which reduces heat transfer through metal to metal contact and also by radiation as the cone 16a acts as a heat-shield. The cone 16a is spaced apart from the tie bar 4 and nut 15 and encloses it to further reduce heat transfer via conduction. It will be appreciated that some embodiments may not require this heat shield.
The rotor moves relative to a stator. This comprises a number of components which will be familiar to the person skilled in the art but in figure 2 there are shown an end plate 19 in the form of an annulus with the rotor 2 protruding through the central hole into the enclosure 5. A labyrinth seal 20 is provided to prevent hot gases escaping into the enclosure cavity. The end plate 19 is also insulated to prevent heat transmission. The stator also includes a series of support spokes 21 two of which can be seen. These are fixed towards the radially outerwards part of the end plate 19 and are inclined inwards in a direction towards the axis of rotation 18. The radially inner ends of the spokes 21 are bolted to an annular shroud 22. This is provided with a central portion which is generally cylindrical which extends in a direction substantially parallel to the axis 18. This part of the arrangement is shown in greater detail in figure 3.
As is shown in figure 3a and 3b, the turbulator cylinder 16, is provided with a plurality of turbulators in the form of ribs 16c milled into its surface. These extend in a parallel direction to the axis. Figure 3b shows that the ribs 16c extend in a radial direction when examined end on from one side. There is a separation 16d between the ribs 16c. Two adjacent ribs are shown enlarged in figure 3c. It can be seen that they are generally rectangular in cross-section and project radially out of the surface on the turbulator cylinder 16. It will be seen that their outermost corner edges are radiused. This is preferred to enhance the coolant flow although other edge profiles may be used.
The preferred rib profile has rib height H from the surface of turbulator cylinder 16 to the radially outermost surface of the rib, a rib spacing or pitch given by the dimension P between the rib centre lines, a rib width of W and there is a clearance to the stator of C where in this case H is given by C/4 and the pitch to height ratio is 10. The geometric ranges may be P/H = range from 5 to 15, C/H=range from 0.1 to 0.5 and W/H=range from 0.3 to 3.0. In this particular case there are seventy two ribs, the pitch P is 5mm, the height H is 0.55 to 0.75mm, the rib width W is 0.5 to 0.75mm, the clearance C is 1.6mm The rib edges have a radius of 0.10 to 0.15mm.
The dimensions for the rib and pitch are chosen to facilitate efficient disturbance to the fluid flow and recombination of the flow to give enhanced cooling. This will now be described with reference to figure 4. The fluid flow is depicted by a simple line but the fluid flow is reality more complex than that depicted. However, as the fluid flow passes over the first rib 16c1 it separates and turbulates over a separation region X and then reattaches over a region Y before flowing over the next rib 16c2. Maximum cooling is effected over the re-attachment region Y. The chosen ratios of dimensions maximise the efficiency of this process.
In the specific embodiment of the invention the sensor signals are passed out of the turbomachine by a slip ring arrangement. It will be appreciated that other non contact methods may be used such as telemeters using wireless methods or memory devices to store the data until downloaded during service of the turbomachine.
In the described embodiment the ribs extend in a direction parallel to the axis of rotation. In alternative embodiments they may be arranged at any angle which may assist in promoting a coolant flow. The turbulators may be placed on the annular shroud in addition to the turbulator cylinder. These may be arranged at opposing angles to further enhance the coolant effect.

Claims

Cl aims
1. A turbomachine comprising a stator (19, 21, 22), a rotor (2, 4, 14, 16, 17), and blade discs (3) mounted on the rotor (2, 4, 14, 16, 17), the rotor (2, 4, 14, 16, 17) being mounted for rotation about an axis (18), the rotation being relative to the stator (19, 21, 22), wherein the rotor (2, 4, 14, 16, 17) includes a turbulator cylinder (16) on the curved external surface of which is provided a plurality of turbulators (16c), wherein the stator (19, 21, 22) includes an annular shroud (22) that extends around the turbulator cylinder (16), the turbulator cylinder (16) and the annular shroud (22) both being concentric with the axis of rotation (18) of the rotor (2, 4, 14, 16, 17), a clearance (C) being defined between adjacent opposed curved surfaces of the turbulator cylinder (16) and annular shroud (22), wherein the plurality of turbulators (16c) provided on the curved external surface of the turbulator cylinder (16) increase heat transfer to a coolant flowing between the adjacent opposed curved surfaces of the turbulator cylinder (16) and annular shroud (22) .
2. A turbomachine as claimed in claim 1 wherein each turbulator (16c) is a longitudinal rib (16c) .
3. A turbomachine as claimed in claim 2 wherein the rib (16c) extends in a direction parallel to the axis of rotation (18) of the rotor (2, 4, 14, 16, 17) .
4. A turbomachine as claimed in any preceding claim wherein the turbulators (16c) have a generally rectangular cross- section .
5. A turbomachine as claimed in claim 4 wherein at least one of the leading and trailing edges of each turbulator (16c) has a radiused profile.
6. A turbomachine as claimed in any preceding claim where each turbulator (16c) has a height (H) which is substantially one quarter of the clearance (C) between the adjacent opposed curved surfaces of the turbulator cylinder (16) and annular shroud (22) .
7. A turbomachine as claimed in any preceding claim wherein the ratio of the pitch (P) of the turbulators (16c) to their height (H) is 10 to 1.
8. A turbomachine as claimed in any preceding claim wherein the turbulators (16c) are arranged to create a separation zone (X) and a reattachment zone (Y) between successive turbulators (16c) to a coolant fluid flow.
9. A turbomachine as claimed in any preceding claim including a heat shield (16a) located within the turbulator cylinder (16) to prevent heat transfer to the turbulator cylinder (16) .
PCT/EP2008/061508 2007-10-01 2008-09-01 A turbomachine WO2009043659A2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP08803486A EP2193256B1 (en) 2007-10-01 2008-09-01 A turbomachine
US12/680,791 US8016555B2 (en) 2007-10-01 2008-09-01 Turbomachine
AT08803486T ATE509187T1 (en) 2007-10-01 2008-09-01 TURBO MACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0718997A GB2453169B (en) 2007-10-01 2007-10-01 A turbomachine
GB0718997.0 2007-10-01

Publications (2)

Publication Number Publication Date
WO2009043659A2 true WO2009043659A2 (en) 2009-04-09
WO2009043659A3 WO2009043659A3 (en) 2009-06-11

Family

ID=38701865

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/061508 WO2009043659A2 (en) 2007-10-01 2008-09-01 A turbomachine

Country Status (6)

Country Link
US (1) US8016555B2 (en)
EP (1) EP2193256B1 (en)
AT (1) ATE509187T1 (en)
GB (1) GB2453169B (en)
RU (1) RU2460887C2 (en)
WO (1) WO2009043659A2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9097122B2 (en) * 2012-01-30 2015-08-04 United Technologies Corporation Turbine engine monitoring system

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US2860827A (en) * 1953-06-08 1958-11-18 Garrett Corp Turbosupercharger
GB866710A (en) * 1956-09-06 1961-04-26 Birmingham Small Arms Co Ltd Improvements in or relating to elastic-fluid turbines
DE1231798B (en) * 1963-07-12 1967-01-05 Licentia Gmbh Direct air-cooled slip ring for an electrical machine, especially a turbo generator
US3476396A (en) * 1964-04-14 1969-11-04 Daimler Benz Ag Shaft seal with return rifling
GB1315302A (en) * 1969-06-10 1973-05-02 Int Research & Dev Co Ltd Rotary electrical machines
JPS585403A (en) * 1981-07-01 1983-01-12 Hitachi Ltd Moving vane for gas turbine
CA1235375A (en) * 1984-10-18 1988-04-19 Nobuo Tsuno Turbine rotor units and method of producing the same
US4740711A (en) * 1985-11-29 1988-04-26 Fuji Electric Co., Ltd. Pipeline built-in electric power generating set
SU1469260A1 (en) * 1985-12-02 1989-03-30 Московский Институт Химического Машиностроения Heat-exchange apparatus
SU1703859A1 (en) * 1989-10-23 1992-01-07 Кооператив "Сириус" Direct-flow centrifugal fan
US5252026A (en) * 1993-01-12 1993-10-12 General Electric Company Gas turbine engine nozzle
US5469817A (en) * 1994-09-01 1995-11-28 Cummins Engine Company, Inc. Turbulator for a liner cooling jacket
US6227800B1 (en) 1998-11-24 2001-05-08 General Electric Company Bay cooled turbine casing
FR2833035B1 (en) * 2001-12-05 2004-08-06 Snecma Moteurs DISTRIBUTOR BLADE PLATFORM FOR A GAS TURBINE ENGINE
EP1734292A1 (en) * 2005-06-13 2006-12-20 Siemens Aktiengesellschaft Sealing means for a turbomachine

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Title
None

Also Published As

Publication number Publication date
GB0718997D0 (en) 2007-11-07
EP2193256B1 (en) 2011-05-11
US20100221103A1 (en) 2010-09-02
ATE509187T1 (en) 2011-05-15
RU2010116396A (en) 2011-11-10
EP2193256A2 (en) 2010-06-09
GB2453169A (en) 2009-04-01
WO2009043659A3 (en) 2009-06-11
GB2453169B (en) 2009-08-12
US8016555B2 (en) 2011-09-13
RU2460887C2 (en) 2012-09-10

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