US20150104316A1 - Turbine blades - Google Patents

Turbine blades Download PDF

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Publication number
US20150104316A1
US20150104316A1 US14/296,611 US201414296611A US2015104316A1 US 20150104316 A1 US20150104316 A1 US 20150104316A1 US 201414296611 A US201414296611 A US 201414296611A US 2015104316 A1 US2015104316 A1 US 2015104316A1
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United States
Prior art keywords
blades
turbomachine
retaining element
turbomachine apparatus
rotor stage
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.)
Abandoned
Application number
US14/296,611
Inventor
Richard Varvill
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Reaction Engines Ltd
Original Assignee
Reaction Engines 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 Reaction Engines Ltd filed Critical Reaction Engines Ltd
Assigned to REACTION ENGINES LTD reassignment REACTION ENGINES LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: VARVILL, Richard
Priority to PCT/GB2014/000403 priority Critical patent/WO2015052467A1/en
Priority to EP14784334.6A priority patent/EP3055508A1/en
Publication of US20150104316A1 publication Critical patent/US20150104316A1/en
Abandoned legal-status Critical Current

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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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the present disclosure relates to rotors for turbomachines such as turbine rotors or compressor rotors and engines including such rotors.
  • SSTO single stage to orbit
  • One example of this may be an aircraft having an engine with two modes of operation: an air-breathing mode and a rocket mode capable of propelling the aircraft to speeds beyond Mach 5, e.g. into orbit.
  • a helium driven, contra-rotating turbine In such an engine, it is envisaged to provide a helium driven, contra-rotating turbine.
  • the turbine drives a compressor to compress intake air taken from atmosphere when the engine is operating in air-breathing mode. It has been challenging to devise a turbine capable of operating at the very high temperatures needed in such an engine since metals cannot endure the temperatures needed by the cycle design and generally result in heavy components. Relative to metals, ceramic materials are generally of low density and can withstand the temperatures involved. However, their low tensile strength and fracture toughness preclude their use in conventional turbine rotors where the blades are attached via a root fixing at the hub, inducing tensile stresses in the blades due to the centrifugal loading.
  • Embodiments of the present disclosure attempt to mitigate at least some of the above-mentioned problems.
  • a turbomachine apparatus (such as a turbine, e.g. for driving a compressor) comprising at least one rotor stage and at least one retaining element, wherein the at least one rotor stage comprises a plurality of blades and is configured to rotate about an axis, and wherein the at least one retaining element is configured to retain the at least one rotor stage with the blades thereof at least partly or wholly in radial compression during rotation thereof.
  • the at least one retaining element may be configured to support a centrifugal load on the at least one rotor stage.
  • the at least one retaining element may be a shroud ring.
  • the at least one retaining element may be formed of a circumferentially-reinforced fibre material.
  • the at least one retaining element may be formed of carbon-carbon (or a matrix of graphite reinforced with carbon fibres). Other materials of suitable strength and weight/density may also be used to form the retaining element.
  • the at least one retaining element may be configured to force the plurality of blades into compression.
  • the plurality of blades may be formed of a ceramic material.
  • the ceramic material may be silicon nitride.
  • the at least one rotor stage may further comprise a hub to which the plurality of blades may be fixed.
  • the turbomachine may be a gas turbine.
  • the gas turbine may be adapted to run on helium.
  • the at least one rotor stage may be adapted to receive gas, such as helium, for example between 900K and 1500K.
  • gas such as helium
  • the temperature may be 1200K being an example.
  • the blades and the at least one retaining element may be separately formed components, which may have been joined together after the separate manufacture thereof.
  • the blades and the at least one retaining element may be joined by diffusion bonding or brazing or any other suitable material joining process.
  • the blades and the hub may be separately formed components, which may have been joined together after the separate manufacture thereof.
  • the blades and the hub may be joined by diffusion bonding.
  • the blades may be configured to withstand a compressive load applied thereto by the at least one retaining element.
  • the blades may be configured to withstand the operational temperature of the turbine substantially without degradation due to temperature.
  • the turbomachine may be a contra-rotating turbine.
  • Another aspect provides a rotor stage having a plurality of blades and at least one retaining element configured to retain the blades in radial compression during rotation thereof.
  • an engine comprising a turbomachine according to previous aspects of the disclosure.
  • a further aspect comprises a flying machine including such an engine.
  • the turbomachine may be a turbine arranged for use in at least an air-breathing mode of the engine.
  • the turbine runs at extremely high temperatures, which traditional metal alloy parts cannot easily endure. Metal parts are also generally of high weight relative to ceramic materials. Ceramic turbine blades are useful due to the favourable temperature resistance and low density of ceramic materials relative to metallic materials. Despite low tensile strength and the brittle nature of ceramic matrix material, the devices in accordance with the embodiments disclosed herein can withstand the loads and temperatures encountered during operation.
  • FIG. 1 shows in cross-section part of a turbine blade arrangement according to an embodiment.
  • FIG. 1 depicts a turbine blade arrangement according to an embodiment.
  • the contra-rotating turbine 100 comprises stator blades 102 , rotor blades 104 , drum 106 and shroud ring 108 .
  • Stator blades 102 and rotor blades 104 are formed of a monolithic ceramic material, for example silicon nitride. In other embodiments, other ceramic materials are used.
  • Shroud ring 108 is formed of a circumferential-fibre-reinforced material, specifically carbon-carbon in the form of a carbon fibre reinforced graphite matrix of material.
  • the carbon-carbon is not oxidised during operation.
  • Carbon-carbon also has a low density relative to metallic materials and suitably high tensile stress relative to monolithic ceramic materials.
  • other materials are used.
  • Each of the components is manufactured separately.
  • components may be manufactured as a single unit.
  • the blades 102 and 104 are joined to the drum 106 and to the shroud ring 108 by diffusion bonding. In other embodiments, other bonding processes are used.
  • helium is passed through the stator and rotor stages of the turbine.
  • the helium may arrive at the turbine at 1200K.
  • the rotor rotates at speeds between 5000 rpm and 20000 rpm.
  • the rotor blades 104 experience a centrifugal load.
  • the load is between 50,000 N/kg and 200,000 N/kg.
  • the rotor blades 104 are fixed at a hub, in the embodiment at around 450 mm from the axis of rotation of the rotor.
  • the hub to tip length of the rotor blades 104 in the embodiment, is around 500 mm.
  • the rotor blades 104 are restrained at the tip by the shroud ring 108 and are forced into compression.
  • the shroud ring 108 carries the centrifugal load of the assembly. As ceramics have poor tensile strength and fracture toughness, the shroud ring 108 reduces the risk of failure of the rotor blades 104 .
  • the circumferential fibres of the shroud ring 108 support the circumferential load present in the shroud ring.
  • Ceramic blades 102 and 104 are able to withstand high temperatures.
  • silicon nitride is capable of withstanding temperatures over 1500K. Therefore the temperature of the helium through the turbine 100 can be increased in relation to conventional turbines. Furthermore, there is no need for cooling of the blades 102 and 104 . Higher temperatures of operation also increase the efficiency of the engine, and reduce specific fuel consumption.
  • Silicon nitride is also of low density relative to metallic materials, thus the weight of the engine is reduced. Furthermore, silicon nitride can be manufactured easily and with a generally smooth surface.
  • Ceramic blades 102 and 104 are also lighter than conventional metal blades. Therefore the centrifugal load on the shroud ring 108 is reduced. The overall weight of the turbine 100 is also reduced. The increased strength to weight ratio of the system permits an increase in turbine tip speed of around 25%, resulting in further improvements in the power to weight ratio of the engine. Joints between the blades 102 and 104 , the drum 106 and the shroud ring 108 may be easily manufactured due to the radial clamping load provided by the radial restraint of the shroud ring 108 .
  • This system is applicable to any turbomachine rotor, for example, axial flow compressors and turbines or centrifugal flow compressors and turbines.
  • Application to high hub/tip ratio turbines may be particularly relevant due to the high resistance to buckling of short turbine blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbomachine apparatus for driving a compressor is disclosed. The turbomachine apparatus contains at least one rotor stage and at least one retaining element. The at least one rotor stage contains a plurality of blades and is configured to rotate about an axis. The at least one retaining element is configured to retain the at least one rotor stage with the blades thereof at least partly or wholly in radial compression during rotation thereof.

Description

    CROSS-REFERENCE TO RELATED APPLICATIONS
  • The present application claims priority under 35 U.S.C. §119(a) to the following application filed in the United Kingdom on Oct. 11, 2013, which is incorporated herein by reference: GB 1318103.7.
    • FIELD
  • The present disclosure relates to rotors for turbomachines such as turbine rotors or compressor rotors and engines including such rotors.
    • BACKGROUND
  • It is commercially desirable to develop a reusable, high-speed, single stage to orbit (SSTO) aircraft. One example of this may be an aircraft having an engine with two modes of operation: an air-breathing mode and a rocket mode capable of propelling the aircraft to speeds beyond Mach 5, e.g. into orbit.
  • In such an engine, it is envisaged to provide a helium driven, contra-rotating turbine. The turbine drives a compressor to compress intake air taken from atmosphere when the engine is operating in air-breathing mode. It has been challenging to devise a turbine capable of operating at the very high temperatures needed in such an engine since metals cannot endure the temperatures needed by the cycle design and generally result in heavy components. Relative to metals, ceramic materials are generally of low density and can withstand the temperatures involved. However, their low tensile strength and fracture toughness preclude their use in conventional turbine rotors where the blades are attached via a root fixing at the hub, inducing tensile stresses in the blades due to the centrifugal loading.
    • SUMMARY
  • Embodiments of the present disclosure attempt to mitigate at least some of the above-mentioned problems.
  • In accordance with a first aspect of the disclosure there is provided a turbomachine apparatus (such as a turbine, e.g. for driving a compressor) comprising at least one rotor stage and at least one retaining element, wherein the at least one rotor stage comprises a plurality of blades and is configured to rotate about an axis, and wherein the at least one retaining element is configured to retain the at least one rotor stage with the blades thereof at least partly or wholly in radial compression during rotation thereof.
  • The at least one retaining element may be configured to support a centrifugal load on the at least one rotor stage.
  • The at least one retaining element may be a shroud ring.
  • The at least one retaining element may be formed of a circumferentially-reinforced fibre material.
  • The at least one retaining element may be formed of carbon-carbon (or a matrix of graphite reinforced with carbon fibres). Other materials of suitable strength and weight/density may also be used to form the retaining element.
  • The at least one retaining element may be configured to force the plurality of blades into compression.
  • The plurality of blades may be formed of a ceramic material.
  • The ceramic material may be silicon nitride.
  • The at least one rotor stage may further comprise a hub to which the plurality of blades may be fixed.
  • The turbomachine may be a gas turbine.
  • The gas turbine may be adapted to run on helium.
  • The at least one rotor stage may be adapted to receive gas, such as helium, for example between 900K and 1500K. In a typical application, the temperature may be 1200K being an example.
  • The blades and the at least one retaining element may be separately formed components, which may have been joined together after the separate manufacture thereof.
  • The blades and the at least one retaining element may be joined by diffusion bonding or brazing or any other suitable material joining process.
  • The blades and the hub may be separately formed components, which may have been joined together after the separate manufacture thereof.
  • The blades and the hub may be joined by diffusion bonding.
  • The blades may be configured to withstand a compressive load applied thereto by the at least one retaining element.
  • The blades may be configured to withstand the operational temperature of the turbine substantially without degradation due to temperature.
  • The turbomachine may be a contra-rotating turbine.
  • Another aspect provides a rotor stage having a plurality of blades and at least one retaining element configured to retain the blades in radial compression during rotation thereof.
  • In accordance with another aspect of the disclosure, there is provided an engine comprising a turbomachine according to previous aspects of the disclosure.
  • A further aspect comprises a flying machine including such an engine.
  • The turbomachine may be a turbine arranged for use in at least an air-breathing mode of the engine.
  • The turbine runs at extremely high temperatures, which traditional metal alloy parts cannot easily endure. Metal parts are also generally of high weight relative to ceramic materials. Ceramic turbine blades are useful due to the favourable temperature resistance and low density of ceramic materials relative to metallic materials. Despite low tensile strength and the brittle nature of ceramic matrix material, the devices in accordance with the embodiments disclosed herein can withstand the loads and temperatures encountered during operation.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • Example embodiments of the disclosure will now be described by way of example only and with reference to the accompanying drawings in which:
  • FIG. 1 shows in cross-section part of a turbine blade arrangement according to an embodiment.
    •
  • Throughout the description and the drawings, like reference numerals refer to like parts.
    • DETAILED DESCRIPTION
  • FIG. 1 depicts a turbine blade arrangement according to an embodiment. The contra-rotating turbine 100 comprises stator blades 102, rotor blades 104, drum 106 and shroud ring 108. Although in the embodiment a contra-rotating turbine is shown, the invention is also applicable to conventional non-contra-rotating turbines or compressors. Stator blades 102 and rotor blades 104 are formed of a monolithic ceramic material, for example silicon nitride. In other embodiments, other ceramic materials are used. Shroud ring 108 is formed of a circumferential-fibre-reinforced material, specifically carbon-carbon in the form of a carbon fibre reinforced graphite matrix of material. As, in the embodiment, helium is used as the working fluid, the carbon-carbon is not oxidised during operation. Carbon-carbon also has a low density relative to metallic materials and suitably high tensile stress relative to monolithic ceramic materials. In other embodiments, other materials are used. Each of the components is manufactured separately. In other embodiments, components may be manufactured as a single unit. The blades 102 and 104 are joined to the drum 106 and to the shroud ring 108 by diffusion bonding. In other embodiments, other bonding processes are used.
  • In operation, helium is passed through the stator and rotor stages of the turbine. The helium may arrive at the turbine at 1200K. The rotor rotates at speeds between 5000 rpm and 20000 rpm. The rotor blades 104 experience a centrifugal load. The load is between 50,000 N/kg and 200,000 N/kg. The rotor blades 104 are fixed at a hub, in the embodiment at around 450 mm from the axis of rotation of the rotor. The hub to tip length of the rotor blades 104, in the embodiment, is around 500 mm. The rotor blades 104 are restrained at the tip by the shroud ring 108 and are forced into compression. The shroud ring 108 carries the centrifugal load of the assembly. As ceramics have poor tensile strength and fracture toughness, the shroud ring 108 reduces the risk of failure of the rotor blades 104. The circumferential fibres of the shroud ring 108 support the circumferential load present in the shroud ring.
  • The excellent properties of ceramics in compression allow the rotor blades 104 to withstand the compressive force. For example, silicon nitride has a compressive strength of around 2500 MPa. The risk of failure of the blades is therefore reduced. Ceramic blades 102 and 104 are able to withstand high temperatures. For example, silicon nitride is capable of withstanding temperatures over 1500K. Therefore the temperature of the helium through the turbine 100 can be increased in relation to conventional turbines. Furthermore, there is no need for cooling of the blades 102 and 104. Higher temperatures of operation also increase the efficiency of the engine, and reduce specific fuel consumption. Silicon nitride is also of low density relative to metallic materials, thus the weight of the engine is reduced. Furthermore, silicon nitride can be manufactured easily and with a generally smooth surface.
  • Ceramic blades 102 and 104 are also lighter than conventional metal blades. Therefore the centrifugal load on the shroud ring 108 is reduced. The overall weight of the turbine 100 is also reduced. The increased strength to weight ratio of the system permits an increase in turbine tip speed of around 25%, resulting in further improvements in the power to weight ratio of the engine. Joints between the blades 102 and 104, the drum 106 and the shroud ring 108 may be easily manufactured due to the radial clamping load provided by the radial restraint of the shroud ring 108.
  • This system is applicable to any turbomachine rotor, for example, axial flow compressors and turbines or centrifugal flow compressors and turbines. Application to high hub/tip ratio turbines may be particularly relevant due to the high resistance to buckling of short turbine blades.
  • Various modifications may be made to the described embodiments without departing from the scope of the invention as defined by the accompanying claims.

Claims (20)

1. A turbomachine apparatus comprising:
at least one rotor stage wherein the rotor stage comprises a plurality of blades and is configured to rotate about an axis; and
at least one retaining element wherein the retaining element is configured to retain the rotor stage with the blades thereof at least partly or wholly in radial compression during rotation thereof.
2. A turbomachine apparatus as claimed in claim 1 wherein the at least one retaining element is configured to support a centrifugal load on the at least one rotor stage.
3. A turbomachine apparatus as claimed in claim 1 wherein the at least one retaining element is a shroud ring.
4. A turbomachine apparatus as claimed in claim 1 wherein the at least one retaining element is formed of a circumferentially-reinforced fiber material.
5. A turbomachine apparatus as claimed in claim 1 wherein the at least one retaining element is formed of carbon-carbon.
6. A turbomachine apparatus as claimed in claim 1 wherein the at least one retaining element is configured to force the plurality of blades into radial compression.
7. A turbomachine apparatus as claimed in claim 1 wherein the plurality of blades is formed of a ceramic material.
8. A turbomachine apparatus as claimed in claim 7 wherein the ceramic material is silicon nitride.
9. A turbomachine apparatus as claimed in claim 1 wherein the at least one rotor stage further comprises a hub.
10. A turbomachine apparatus as claimed in claim 9 wherein the plurality of blades is fixed to the hub.
11. A turbomachine apparatus as claimed in claim 1 wherein the plurality of blades and the at least one retaining element are separately formed components.
12. A turbomachine apparatus as claimed in claim 11 wherein the blades and the at least one retaining element are joined by diffusion bonding or brazing.
13. A turbomachine apparatus as claimed in claim 1, wherein the at least one rotor stage further comprises a hub and wherein the plurality of blades and the hub are separately formed components.
14. A turbomachine apparatus as claimed in claim 13 wherein the blades and the hub are joined by diffusion bonding or brazing or other suitable material joining process.
15. A turbomachine apparatus as claimed in claim 1 wherein the turbomachine apparatus comprises a gas turbine.
16. A turbomachine apparatus as claimed in claim 15 wherein the gas turbine is configured to run on helium or another inert fluid.
17. A turbomachine apparatus as claimed in claim 15 wherein at least one of the at least one rotor stages is adapted to receive gas, such as helium, at around 1200K.
18. A turbomachine apparatus as claimed in claim 1 wherein the plurality of blades is configured to withstand a compressive load applied thereto by the at least one retaining element.
19. A turbomachine apparatus as claimed in claim 1 wherein the blades are configured to withstand the operational temperature of the turbomachine apparatus without substantial degradation due to temperature.
20. A turbomachine apparatus as claimed in claim 1 which comprises a contra-rotating turbine.
US14/296,611 2013-10-11 2014-06-05 Turbine blades Abandoned US20150104316A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/GB2014/000403 WO2015052467A1 (en) 2013-10-11 2014-10-10 Turbine blades
EP14784334.6A EP3055508A1 (en) 2013-10-11 2014-10-10 Turbine blades

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1318103.7A GB2521588A (en) 2013-10-11 2013-10-11 Turbine blades
GB1318103.7 2013-10-11

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GB201318103D0 (en) 2013-11-27

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