CN105275513B - Turbine part - Google Patents
Turbine part Download PDFInfo
- Publication number
- CN105275513B CN105275513B CN201510294617.3A CN201510294617A CN105275513B CN 105275513 B CN105275513 B CN 105275513B CN 201510294617 A CN201510294617 A CN 201510294617A CN 105275513 B CN105275513 B CN 105275513B
- Authority
- CN
- China
- Prior art keywords
- hook portion
- shield
- outer shield
- interior
- turbine part
- 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.)
- Active
Links
- 239000000919 ceramic Substances 0.000 claims abstract description 24
- 239000002131 composite material Substances 0.000 claims abstract description 20
- 239000000835 fiber Substances 0.000 claims abstract description 20
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 19
- HPNSNYBUADCFDR-UHFFFAOYSA-N chromafenozide Chemical compound CC1=CC(C)=CC(C(=O)N(NC(=O)C=2C(=C3CCCOC3=CC=2)C)C(C)(C)C)=C1 HPNSNYBUADCFDR-UHFFFAOYSA-N 0.000 claims description 11
- 238000000576 coating method Methods 0.000 claims description 10
- 229910018540 Si C Inorganic materials 0.000 claims description 7
- 239000011248 coating agent Substances 0.000 claims description 7
- 230000035939 shock Effects 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 6
- 239000011159 matrix material Substances 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 4
- 239000000463 material Substances 0.000 description 21
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 9
- 238000001816 cooling Methods 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 239000011153 ceramic matrix composite Substances 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 238000010248 power generation Methods 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229910052727 yttrium Inorganic materials 0.000 description 2
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 241000208340 Araliaceae Species 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 229910052769 Ytterbium Inorganic materials 0.000 description 1
- WOIHABYNKOEWFG-UHFFFAOYSA-N [Sr].[Ba] Chemical compound [Sr].[Ba] WOIHABYNKOEWFG-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910000323 aluminium silicate Inorganic materials 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 1
- 238000007766 curtain coating Methods 0.000 description 1
- HNPSIPDUKPIQMN-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Al]O[Al]=O HNPSIPDUKPIQMN-UHFFFAOYSA-N 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 125000001820 oxy group Chemical group [*:1]O[*:2] 0.000 description 1
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- NAWDYIZEMPQZHO-UHFFFAOYSA-N ytterbium Chemical compound [Yb] NAWDYIZEMPQZHO-UHFFFAOYSA-N 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
- 229910001928 zirconium oxide Inorganic materials 0.000 description 1
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
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- 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]
Abstract
Disclose a kind of turbine part.Turbine part includes outer shield and interior shield, which has：First hook portion region, extends above the first part of outer shield；With the second hook portion region, extend above the second part of outer shield.First hook portion gap, the second hook portion gap, the first radial clearance and the second radial clearance configure and are arranged as that interior shield is allowed to deviate outer shield under heat load.In addition or alternatively, interior shield includes ceramic based composite fibre, has the pyroconductivity less than 200W/m k and more than 10W/m k.
Description
Technical field
The present invention relates to turbine parts.More particularly, it relates to the turbine part with interior shield and outer shield.
Background technology
The higher temperature and pressure operation of turbine part in turbogenerator and power generation system allows to improve
Efficiency and the operation in neotectonics.The material that can be operated under this higher temperature and pressure is selected to be difficult.
This material may be both expensive, be difficult to produce or be difficult to make.In addition, the use of this different materials can need
Modification to cooling body, this can generate other complications.
General it is desired that using less material for similar or better operation.Weight is reduced using less material
Relevant cost is measured, reduced and manufactured, material cost is reduced and several further advantages is provided.But use is less
The power not being expected to that material can generate complicated geometry requirement and/or not generated before can generating, such as stress.In addition, such as
The case where for using different materials, can need the complicated and/or high modification to cooling body using less material,
This can generate other complications.
Thus, there is the constant demand to producing following material：It can be subjected to higher temperature and pressure；It can be with lower
Amount/weight applied；It can be operated without generating the power not being expected to；And it can in the operating condition use without adopting
With complicated and/or high cooling body.
Show that one or more improved turbine parts will be expected in the art compared with prior art.
Invention content
In embodiment, turbine part includes outer shield and interior shield, which has：First hook portion region,
Extend above the first part of outer shield；With the second hook portion region, extend above the second part of outer shield.First hook portion
Region and first part limit the first hook portion gap, and the second hook portion region and second part limit the second hook portion gap.First
Radial clearance extends between the first hook portion region opposite with the first hook portion gap and outer shield, and the second radial clearance with
Extend between the second opposite hook portion region of second hook portion gap and outer shield.First hook portion gap, the second hook portion gap, first
Radial clearance and the second radial clearance configure and are arranged as that interior shield is allowed to deviate outer shield under heat load.
In another embodiment, turbine part includes outer shield and interior shield, which has：First hook portion region,
It extends above the first part of outer shield；With the second hook portion region, extend above the second part of outer shield.Interior shield
Cover includes ceramic based composite fibre, has the pyroconductivity less than 200W/m k and more than 10W/m k.
In another embodiment, turbine part includes outer shield and interior shield, which has：First hook portion region,
It extends above the first part of outer shield；With the second hook portion region, extend above the second part of outer shield.First
Hook portion region and first part limit the first hook portion gap, and the second hook portion region and second part limit the second hook portion gap,
And the first hook portion gap, the second hook portion gap configure and are arranged as that interior shield is allowed to deviate outer shield under heat load.Interior shield
Cover includes ceramic based composite fibre, has the pyroconductivity less than 200W/m k and more than 10W/m k.
The first technical solution of the present invention is a kind of turbine part comprising：Outer shield；And interior shield, have：The
One hook portion region, extends above the first part of outer shield；With the second hook portion region, on the second part of outer shield
Fang Yanshen；Wherein, the first hook portion region and first part limit the first hook portion gap, and the second hook portion region and second part limit
Fixed second hook portion gap；Wherein, the first radial clearance the first hook portion region opposite with the first hook portion gap and outer shield it
Between extend, and the second radial clearance extends between the second hook portion region opposite with the second hook portion gap and outer shield；Wherein,
First hook portion gap, the second hook portion gap, the first radial clearance and the second radial clearance configure and are arranged as allowing interior shield
Deviate outer shield under heat load.
The second technical solution of the present invention is that in the first technical solution of the present invention, interior shield includes that ceramic base is compound
Material.
The third technical solution of the present invention is that in the second technical solution of the present invention, ceramic matric composite includes Si-
Fiber C and SiC matrix.
The 4th technical solution of the present invention is that in the third technical solution of the present invention, Si-C fibers are compound in ceramic base
By volume at least 20% concentration in object.
The 5th technical solution of the present invention is that in the first technical solution of the present invention, outer shield includes metal or metal
Property material.
The 6th technical solution of the present invention is, in the first technical solution of the present invention, interior shield, which has, is less than 200W/m
The pyroconductivity of k.
The 7th technical solution of the present invention is, in the first technical solution of the present invention, interior shield, which has, is more than 10W/m k
Pyroconductivity.
The 8th technical solution of the present invention is, in the first technical solution of the present invention, interior shield has about 120W/m
The pyroconductivity of k.
The 9th technical solution of the present invention is that in the first technical solution of the present invention, interior shield and outer shield are in turbine
It is not coupled during the operation of component.
The tenth technical solution of the present invention is that in the first technical solution of the present invention, turbine part further includes shock plate,
It is located between interior shield and outer shield.
The 11st technical solution of the present invention is that in the tenth technical solution of the present invention, shock plate includes metal.
The 12nd technical solution of the present invention is that in the first technical solution of the present invention, outer shield includes internal cavity.
The 13rd technical solution of the present invention is, in the 12nd technical solution of the present invention, internal cavity is pressurized.
The 14th technical solution of the present invention is that in the 13rd technical solution of the present invention, internal cavity is pressurized to
In or more than hot gas path pressure pressure.
The 15th technical solution of the present invention is that in the first technical solution of the present invention, turbine part further includes transverse direction
Gap extends parallel between the first hook portion region and the second hook portion region at least part of interior shield.
The 16th technical solution of the present invention is that in the first technical solution of the present invention, turbine part further includes adding
Interior shield, be positioned as shield in adjacent, and extend above the first part of outer shield and the second part of outer shield.
The 17th technical solution of the present invention is that in the first technical solution of the present invention, turbine part further includes environment
Curtain coating, being positioned at will be in at least part for the interior shield that contacted by hot gas path.
The 18th technical solution of the present invention is that in the 17th technical solution of the present invention, environment shielding coating is can
Wear away friction coatings.
The 19th technical solution of the present invention is a kind of turbine part comprising：Outer shield；And interior shield, have：
First hook portion region, extends above the first part of outer shield；With the second hook portion region, in the second part of outer shield
Top extends；Wherein, interior shield includes ceramic based composite fibre, and there is the heat less than 200W/m k and more than 10W/m k to pass
Conductance.
The 20th technical solution of the present invention is a kind of turbine part comprising：Outer shield；And interior shield, have：
First hook portion region, extends above the first part of outer shield；With the second hook portion region, in the second part of outer shield
Top extends；Wherein, the first hook portion gap of the first hook portion region and first part's restriction, and the second hook portion region and second part
The second hook portion gap is limited, and the first hook portion gap and the second hook portion gap configure and be arranged as allowing interior shield in heat load
Lower deviation outer shield；Wherein, interior shield includes ceramic based composite fibre, is had less than 200W/m k and more than 10W/m k's
Pyroconductivity.
Other features and advantages of the present invention will become obvious from the following more detailed description carried out in conjunction with attached drawing,
Attached drawing shows the principle of the present invention by means of example.
Description of the drawings
Fig. 1 is the perspective view according to the embodiment of the component with interior shield and outer shield of the disclosure.
Whenever possible, identical part will be represented using identical label through attached drawing.
Specific implementation mode
Provide a kind of turbine part.Such as it is one or more in disclosed feature with failing to be included herein
Principle is compared, and embodiment of the disclosure can carry out simpler reparation or replacement, can be subjected to higher temperature and pressure, energy
It is enough with lower amount/weight application, can be operated without generate the power not being expected to, can use in the operating condition and
Not using complicated and/or high cooling body, and/or it can carry out mechanical load and reduce leakage, thus enhance and start
Machine operating efficiency.
Fig. 1 show for example can power generation system, turbogenerator, or both in the turbine part 100 that uses
Embodiment.Turbine part 100 includes outer shield 101 and interior shield 103, which has：First hook portion region 105,
It extends above the first part 109 of outer shield 101；With the second hook portion region 107, in the second part of outer shield 101
111 tops extend.First hook portion gap 113 of first hook portion region 105 and the restriction of first part 109, and the second hook portion region 107
The second hook portion gap 115 is limited with second part 111.First radial clearance 114 is opposite with the first hook portion gap 113 first
Extend between hook portion region 105 and outer shield 101, and the second radial clearance 116 is opposite with the second hook portion gap 115 second
Extend between hook portion region 107 and outer shield 101.First hook portion gap 113, the second hook portion gap 115, the first radial clearance
114 and second radial clearance 116 configuration and be arranged as that interior shield 103 is allowed to deviate outer shield 101 under heat load.
First hook portion gap 113, the second hook portion gap 115, the first radial clearance 114 and the second radial clearance 116 are
Allow to deviate any geometry appropriate of stress to be reduced or eliminated during the operating with of turbine part 100.For example,
In one embodiment, geometry appropriate is included the cuboid channel that the top of shield 103 extends.Although having used art
Language " hook portion ", and Fig. 1 shows the first bending part 102, immediately the first flat 104 of the first bending part 102, tight
Connect the second bending part 106 of the first flat 104, the second flat 108 of immediately the second bending part 106, wherein
Second flat 108 is in substantially parallel relationship to interior shield and hot gas path 119 and extends it should be appreciated that extend into
The angled, arciform of plane, curling, curve or the other configurations of few three separation should be considered in term " hook portion ".Its
Its geometry appropriate include but not limited to rectangular cylinder, slit, cylinder (for example, semicolumn) part, with connection
The bow portion on the flat or generally flat boundary of the end in bow portion, or any other geometry deviateed is provided.
First hook portion region 105, the first radial clearance 114 and the first part 109 immediately leading edge compared with rear 129
127.Second hook portion region 107, the second radial clearance 116 and second part 111 immediately rear 129 compared with leading edge 127.
Interior shield 103 is adjustably fixed to outer shield 101 by the first hook portion region 105 and the second hook portion region 107.Implement at one
In example, interior shield 103 and outer shield 101 can be fixed together and without being bolted, by relying on outer shield 101
109 top of first part the first hook portion region 105 extended and extend above the second part 111 of outer shield 101 second
Hook portion region 107.Any other power appropriate provide mechanism can be used for further fixing outer shield 101 and interior shield 103, with
And other interior shields in the embodiment with multiple interior shields 103.
In one embodiment, in conjunction with the outer shield 101 of the material of selection and interior shield 103 configuration allow in shield
103 remove from the selectivity of outer shield 101, repair, and/or replace.For example, in one embodiment, interior shield 103 and outer shield
Cover 101 is not coupled under the operating condition appropriate of turbine part 100.As used in this article, term " connection " means
Such as the local buckling or deformation of the outer shield 101 above the second flat 108.Operating condition appropriate includes but unlimited
On from 1200 °F to 3200 °F (on about 650 DEG C to 1760 DEG C).
Interior shield 103 and outer shield 101 are including that in power generation system, turbogenerator or can utilize turbine part
Any material appropriate used in the operating condition of 100 any other system.In one embodiment, outer shield 101 wraps
Metal or metallic alloy are included, for example, nickel-base alloy or stainless steel.In one embodiment, interior shield 103 is multiple including ceramic base
Close object.As used in this article, term " ceramic matrix composite " includes but not limited to carbon-fiber reinforced carbon (C/C), carbon fiber
Dimension enhancing silicon carbide (C/SiC), silicon carbide fiber reinforced silicon carbide (SiC/SiC) and silicon carbide fibre enhancing oxygroup are compound
Object.In one embodiment, ceramic matric composite compared with layered ceramic structure have increased elongation, fracture toughness,
Thermal shock, dynamic load ability and anisotropic properties.A kind of ceramic matrix composite appropriate includes SiC-C fibers and SiC
Matrix is in following concentration in ceramic matrix composite for example, carrying SiC fibers by volume：At least about 20%, for example,
At least about 23%, at least about 28%, at least about 30%, between about 23% and about 32%, or wherein appoint
What combination, sub-portfolio, range or subrange appropriate.
The material for interior shield 103 is selected to provide the pyroconductivity of the range of choice for turbine part 100.One
In a embodiment, the pyroconductivity of interior shield 103 and/or the material for interior shield 103 is less than 200W/m k, is less than 150W/
M k, any combination, sub-portfolio, range or subrange appropriate less than 140W/m k, less than 130W/m k or wherein.This
Outside or alternatively, in one embodiment, the pyroconductivity of interior shield 103 and/or the material for interior shield 103 is more than 10W/
M k, any combination appropriate less than 50W/m k, more than 100W/m k, less than 110W/m k or wherein, sub-portfolio, model
It encloses or subrange.In one embodiment, pyroconductivity is 120W/m k.
Interior shield 103 and/or outer shield 101 include any other feature appropriate, can not adversely under heat load
It influences to deviate.For example, in one embodiment, outer shield 101 includes internal cavity 117, allows fluid (for example, air or pressure
Contracting air) flowing.Internal cavity 117 can for example be sealed by the spline on the circumferential surface of turbine part 100 and in leading edge
127 and/or on rear 129 compliance sealing and sealed.In one embodiment, such as by internal cavity 117 it is forced into
Or operating pressure and/or pressure higher than hot gas path 119, the hot gas path 119 along interior shield 103 distal portions
Opposite outer shield 101 is cross-section.In one embodiment, lateral clearance 121 is from the first hook portion region 105 to the second hook portion region
107 parallel, general parallel orientation or tangentially extend between interior shield 103 and outer shield 101, and allow heat from interior shield 103
It is transferred to outer shield 101.In another embodiment, shock plate 123 is positioned between interior shield 103 and outer shield 101.Shock plate
123 include identical as interior shield 103, similar or different material, and provides cooling by transmitting heat to internal cavity 117.
Interior shield 103 comes including any feature appropriate in response to operating parameter (for example, temperature and pressure), operation ginseng
Number is derived from the hot gas contact being positioned as by hot gas path 119.For example, in one embodiment, interior shield 103 includes
Environment shielding coating 125 is located on some or all surfaces of interior shield 103, which is positioned to and in hot gas
Hot gas contact in body path 119.Environment shielding coating 125 is times that can carry out the operation in hot gas path 119
What coating appropriate.In order to adapt to vane tip gap, in one embodiment, the interior shield 103 in hot gas path 119
Upper includes abradable friction coatings (not shown).For environment shielding coating 125 and/or the material appropriate of abradable friction coatings
Material includes but not limited to strontium barium aluminosilicate, mullite, yttrium stable zirconium oxide, yttrium monocrystalline (yttria mono) and two silicon
Hydrochlorate, ytterbium monocrystalline (yterbium mono) and dislicata and combination thereof.
Although describing the present invention by reference to one or more embodiments, those skilled in the art will be understood that,
It can carry out various changes and replace equivalent without departing from the scope of the present invention for their element.In addition, many can be carried out
It changes so that specific condition or material adapt to basic categories of the teachings of the present invention without departing from them.Therefore, it is intended that be, this
Invention is not limited to the open specific embodiment as the optimal mode visualized for implementing the present invention, but the present invention will wrap
Include all embodiments fallen within the scope of the appended claims.
Claims (16)
1. a kind of turbine part, including：
Outer shield；And
Interior shield, the interior shield close on the hot gas path with hot gas pressure, and the interior shield has：First hook portion area
Domain extends above the first part of the outer shield；With the second hook portion region, on the second part of the outer shield
Fang Yanshen；
Wherein, first hook portion region and the first part limit the first hook portion gap, and second hook portion region and
The second part limits the second hook portion gap；
Wherein, the first radial clearance first hook portion region opposite with first hook portion gap and the outer shield it
Between extend, and the second radial clearance second hook portion region opposite with second hook portion gap and the outer shield it
Between extend；
Wherein, first hook portion gap, second hook portion gap, first radial clearance and second radial direction
Gap configures and is arranged as that the interior shield is allowed to deviate the outer shield under heat load；
Wherein, the interior shield includes ceramic matric composite, and the ceramic matric composite includes Si-C fibers and SiC bases
Matter, the Si-C fibers are in dense between about 23% and about 32% in the ceramic matric composite by volume
Degree.
2. turbine part according to claim 1, which is characterized in that the outer shield includes metal or metallic alloy.
3. turbine part according to claim 1, which is characterized in that there is the interior shield heat less than 200W/mk to pass
Conductance.
4. turbine part according to claim 1, which is characterized in that the interior shield has the heat transfer more than 10W/mk
Rate.
5. turbine part according to claim 1, which is characterized in that the interior shield and the outer shield are in turbine part
Operation during be not coupled.
6. turbine part according to claim 1, which is characterized in that further include shock plate, be located in the interior shield
Between the outer shield.
7. turbine part according to claim 6, which is characterized in that the shock plate includes metal.
8. turbine part according to claim 1, which is characterized in that the outer shield includes internal cavity.
9. turbine part according to claim 8, which is characterized in that the internal cavity is pressurized.
10. turbine part according to claim 9, which is characterized in that the internal cavity is pressurized to equal to or more than institute
State the pressure of hot gas path pressure.
11. turbine part according to claim 1, which is characterized in that further include lateral clearance, in first hook portion
At least part between region and second hook portion region with the interior shield extends parallel to.
12. turbine part according to claim 1, which is characterized in that further include additional interior shield, be positioned as abutting
The interior shield, and extend above the first part of the outer shield and the second part of the outer shield.
13. turbine part according to claim 1, which is characterized in that further include environment shielding coating, be positioned at quilt
In at least part of the interior shield of the hot gas path contact.
14. turbine part according to claim 13, which is characterized in that the environment shielding coating is that abradable friction applies
Layer.
15. a kind of turbine part, including：
Outer shield；And
Interior shield, has：First hook portion region, extends above the first part of the outer shield；With the second hook portion area
Domain extends above the second part of the outer shield；
Wherein, the interior shield includes ceramic matric composite, and the ceramic matric composite is included in the Si-C in SiC matrix
The ceramic based composite fibre of fiber, the ceramics based composite fibre have the pyroconductivity less than 200W/mk and more than 10W/mk；
And
Wherein, the Si-C fibers are in by volume between about 23% and about 32% in the ceramic matric composite
Concentration.
16. a kind of turbine part, including：
Outer shield；And
Interior shield, has：First hook portion region, extends above the first part of the outer shield；With the second hook portion area
Domain extends above the second part of the outer shield；
Wherein, first hook portion region and the first part limit the first hook portion gap, and second hook portion region and
The second part limits the second hook portion gap, and first hook portion gap and the configuration of second hook portion gap and arrangement
To allow the interior shield to deviate the outer shield under heat load；
Wherein, the interior shield includes ceramic matric composite, and the ceramic matric composite is included in the Si-C in SiC matrix
The ceramic based composite fibre of fiber, the ceramics based composite fibre have the pyroconductivity less than 200W/mk and more than 10W/mk；
And
Wherein, the Si-C fibers are in by volume between about 23% and about 32% in the ceramic matric composite
Concentration.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/292,985 US20150345308A1 (en) | 2014-06-02 | 2014-06-02 | Turbine component |
| US14/292985 | 2014-06-02 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105275513A CN105275513A (en) | 2016-01-27 |
| CN105275513B true CN105275513B (en) | 2018-07-24 |
Family
ID=54481601
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510294617.3A Active CN105275513B (en) | 2014-06-02 | 2015-06-02 | Turbine part |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150345308A1 (en) |
| JP (1) | JP6979751B2 (en) |
| CN (1) | CN105275513B (en) |
| CH (1) | CH709761B1 (en) |
| DE (1) | DE102015107848A1 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170276000A1 (en) * | 2016-03-24 | 2017-09-28 | General Electric Company | Apparatus and method for forming apparatus |
| US10519790B2 (en) * | 2017-06-15 | 2019-12-31 | General Electric Company | Turbine shroud assembly |
| US10711637B2 (en) * | 2017-06-15 | 2020-07-14 | General Electric Company | Turbine component assembly |
| WO2019215913A1 (en) | 2018-05-11 | 2019-11-14 | 川崎重工業株式会社 | Shroud assembly for gas turbine |
| US11097384B2 (en) * | 2019-01-23 | 2021-08-24 | General Electric Company | Mechanical ceramic matrix composite (CMS) repair |
| US11248482B2 (en) | 2019-07-19 | 2022-02-15 | Raytheon Technologies Corporation | CMC BOAS arrangement |
| US11073038B2 (en) | 2019-07-19 | 2021-07-27 | Raytheon Technologies Corporation | CMC BOAS arrangement |
| US11073037B2 (en) | 2019-07-19 | 2021-07-27 | Raytheon Technologies Corporation | CMC BOAS arrangement |
| US11105214B2 (en) * | 2019-07-19 | 2021-08-31 | Raytheon Technologies Corporation | CMC BOAS arrangement |
| US11326469B2 (en) * | 2020-05-29 | 2022-05-10 | Rolls-Royce Corporation | CMCs with luminescence environmental barrier coatings |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6702550B2 (en) * | 2002-01-16 | 2004-03-09 | General Electric Company | Turbine shroud segment and shroud assembly |
| US6758653B2 (en) * | 2002-09-09 | 2004-07-06 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
| US7012035B2 (en) * | 2002-02-06 | 2006-03-14 | Mt Aerospace Ag | Fibre composite ceramic with a high thermal conductivity |
| US8147192B2 (en) * | 2008-09-19 | 2012-04-03 | General Electric Company | Dual stage turbine shroud |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10331602A (en) * | 1997-05-29 | 1998-12-15 | Toshiba Corp | Gas turbine |
| US7090459B2 (en) * | 2004-03-31 | 2006-08-15 | General Electric Company | Hybrid seal and system and method incorporating the same |
| US7063503B2 (en) * | 2004-04-15 | 2006-06-20 | Pratt & Whitney Canada Corp. | Turbine shroud cooling system |
| FR2949810B1 (en) * | 2009-09-04 | 2013-06-28 | Turbomeca | DEVICE FOR SUPPORTING A TURBINE RING, TURBINE WITH SUCH A DEVICE AND TURBOMOTOR WITH SUCH A TURBINE |
| US20120076927A1 (en) * | 2010-02-01 | 2012-03-29 | United States Government As Represented By The Secretary Of The Army | Method of improving the thermo-mechanical properties of fiber-reinforced silicon carbide matrix composites |
| US8905709B2 (en) * | 2010-09-30 | 2014-12-09 | General Electric Company | Low-ductility open channel turbine shroud |
-
2014
- 2014-06-02 US US14/292,985 patent/US20150345308A1/en not_active Abandoned
-
2015
- 2015-05-19 DE DE102015107848.1A patent/DE102015107848A1/en active Pending
- 2015-05-26 JP JP2015105952A patent/JP6979751B2/en active Active
- 2015-05-27 CH CH00753/15A patent/CH709761B1/en unknown
- 2015-06-02 CN CN201510294617.3A patent/CN105275513B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6702550B2 (en) * | 2002-01-16 | 2004-03-09 | General Electric Company | Turbine shroud segment and shroud assembly |
| US7012035B2 (en) * | 2002-02-06 | 2006-03-14 | Mt Aerospace Ag | Fibre composite ceramic with a high thermal conductivity |
| US6758653B2 (en) * | 2002-09-09 | 2004-07-06 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
| US8147192B2 (en) * | 2008-09-19 | 2012-04-03 | General Electric Company | Dual stage turbine shroud |
Also Published As
| Publication number | Publication date |
|---|---|
| US20150345308A1 (en) | 2015-12-03 |
| CH709761B1 (en) | 2019-07-15 |
| DE102015107848A1 (en) | 2015-12-03 |
| CN105275513A (en) | 2016-01-27 |
| JP2015227661A (en) | 2015-12-17 |
| JP6979751B2 (en) | 2021-12-15 |
| CH709761A2 (en) | 2015-12-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105275513B (en) | Turbine part | |
| US6932566B2 (en) | Gas turbine shroud structure | |
| CN105518255B (en) | For the integrated form platform and the synusia framework of damper holding structure in CMC turbo blades | |
| US7726936B2 (en) | Turbine engine ring seal | |
| CN106481370B (en) | Sealing groove mouth system of coating for turbine and forming method thereof | |
| US10563523B2 (en) | Method for fabricating a ceramic matrix composite rotor blade | |
| CN106894845B (en) | Cooling circuit for multiwall vane | |
| JP6397172B2 (en) | Layered array, hot gas path components, and process for forming a layered array | |
| EP2503103B1 (en) | Steam turbine | |
| JP6920793B2 (en) | Seal with coating compatible with turbomachinery | |
| EP2543826A2 (en) | Composite shroud | |
| US20100150703A1 (en) | Stacked laminate bolted ring segment | |
| EP1939428A2 (en) | Flame prevention device | |
| US10273813B2 (en) | Ceramic matrix composite component and process of producing a ceramic matrix composite component | |
| Gerenda´ s et al. | Improvement of oxide/oxide CMC and development of combustor and turbine components in the HiPOC program | |
| CN106468189A (en) | Turbomachine shroud assembly | |
| US20200072066A1 (en) | Turbine vane assembly with ceramic matrix composite components mounted to case | |
| CN109642467A (en) | Turbine system with seal member | |
| CN106523160B (en) | Turbine shroud assembly and method for loading | |
| CN110268098A (en) | The thermal barrier coating system compatible with coating | |
| US20130089431A1 (en) | Airfoil for turbine system | |
| US20090235667A1 (en) | Gas-turbine combustion chamber with ceramic flame tube | |
| CN107532483A (en) | Include the turbine ring assemblies of multiple ring sectors made of ceramic matrix composites | |
| BR112020006473B1 (en) | METHOD FOR PRODUCING A HOLLOW PART MADE OF A COMPOSITE MATERIAL WITH CERAMIC MATRIX | |
| US20190119172A1 (en) | Coating structure, turbine part having same, and method for manufacturing coating structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240111 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York State, USA Patentee before: General Electric Co. |