EP3132202B1 - Element de bouclier thermique avec contournement - Google Patents

Element de bouclier thermique avec contournement Download PDF

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Publication number
EP3132202B1
EP3132202B1 EP16713409.7A EP16713409A EP3132202B1 EP 3132202 B1 EP3132202 B1 EP 3132202B1 EP 16713409 A EP16713409 A EP 16713409A EP 3132202 B1 EP3132202 B1 EP 3132202B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
combustion chamber
wall
edge
shield element
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.)
Not-in-force
Application number
EP16713409.7A
Other languages
German (de)
English (en)
Other versions
EP3132202A1 (fr
Inventor
Andreas Böttcher
Andre Kluge
Tobias Krieger
Kaspar Matthias MALECHA
Youssef MOUJANE
Kai-Uwe Schildmacher
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Publication of EP3132202A1 publication Critical patent/EP3132202A1/fr
Application granted granted Critical
Publication of EP3132202B1 publication Critical patent/EP3132202B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the invention relates to a heat shield element, in particular for lining a combustion chamber.
  • the invention further relates to an annular combustion chamber and a gas turbine plant.
  • the gas turbine operator may be forced to shut down its gas turbine if it is unable to further reduce its gas turbine power without exceeding the carbon monoxide emission limit.
  • bypass air into the combustion chamber ie from compressor discharge air, which is diverted in front of the burner and guided into the combustion chamber behind the combustion zone, is remedied.
  • the walls of high temperature gas reactors such as pressurized gas turbine combustors, require suitable shielding of their support structure against attack by the hot gas. Due to their high temperature resistance, corrosion resistance and their low thermal conductivity compared to metallic materials, ceramic materials are particularly suitable for building up a heat shield shielding the support structure.
  • a heat shield is for example in EP 0 558 540 B1 and would have to be modified accordingly in the implementation of a bypass of the compressor discharge air.
  • the heat shield element has a wall with a hot side facing the combustion chamber and an opposite cold side.
  • a circumferential edge extends beyond the cold side on the back. It is provided that in the peripheral edge a plurality of bores are introduced, can flow through the cooling air into the combustion chamber.
  • a second partial wall is present, which extends between two opposite edge portions. However, a downstream edge portion of the peripheral edge extends only to the partial wall and not beyond.
  • a partition wall is arranged, which extends from the partial wall to the rear height of the two adjacent edge portions. This also makes it possible to guide a bypass air flow on the partial wall, which can then emerge downstream between the opposite edge portions.
  • An object of the invention is therefore to provide a heat shield element which allows the supply of bypass air, at the same time high life and as possible easy and inexpensive to manufacture and assemble.
  • Another object of the invention is to provide an annular combustion chamber with a corresponding heat shield.
  • the generic heat shield element is used in particular for use as a lining of a combustion chamber.
  • the heat shield element initially comprises a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side.
  • the heat shield element comprises an edge adjacent to the wall and surrounding the wall. In this case, the edge extends from the hot side pointing away raised above the cold side.
  • the edge can be divided into two opposing first edge portions.
  • At one end of the wall is a second edge portion, which connects the two first edge portions with each other and extends substantially transverse to the first edge portions.
  • a third edge portion Opposite to the second edge portion is a third edge portion, which also connects the two first edge portions with each other and extends substantially transverse to the first edge portions.
  • the wall has at least one opening gap, whereby the wall in a first wall portion on one side of the opening gap and a second wall portion the other side of the opening gap is divided. Furthermore, it is provided that adjoins the second wall portion adjacent to the opening gap from the hot side pioneering partition.
  • the second wall section on the cold side is surrounded by sections of the two first edge sections, the second edge section and the partition wall arranged opposite the second edge section.
  • the first wall section is surrounded by likewise the two first edge sections in sections, the third edge section and the opening gap arranged opposite the third edge section adjacent to the dividing wall.
  • first and second chambers are formed on the cold side of the wall, wherein the first chamber has an opening gap from the cold side to the hot side.
  • the interior of the heat shield element is divided into two parts.
  • the first chamber acts as an extension of the bypass channel.
  • the heat shield element fits homogeneously into the bypass. Characterized in that the opening gap directly adjacent to the partition wall in particular a small distance between a bypass channel and the ⁇ fftsspalt a homogeneous flow pattern is promoted with low pressure drop across the opening gap.
  • the opening gap extends along the entire partition between the two opposite first edge portions, so that a uniform bypass flow with sufficient mass flow can be achieved.
  • the shape or the course of the peripheral edge and the partition on the cold side is initially irrelevant.
  • the edge portions and the partition wall to each other and / or within the sections kinks or jumps and thus have a different height on the cold side.
  • the circulating Edge and the partition extends to a remote from the cold side free end.
  • the free end corresponds to a surface which is at a distance from the hot side or from the cold side (without kinks or jumps).
  • the free end is planar.
  • the planar shape of the heat shield element on the rear facing away from the hot side favors both the assembly and the production.
  • the partition wall is inclined towards the opening gap.
  • the partition wall when viewing the heat shield element from the hot side, the partition wall is located over the opening gap in sections.
  • a neutral discharge angle of the bypass flow can be realized when entering the combustion chamber, since the bypass air must otherwise flow against the combustion gas.
  • the gap would otherwise open to the flame and would provoke the entry of hot gas.
  • the partition wall has a plurality of bores whose axes are directed onto the surface of the cold side of the first wall section. If the second chamber is designed comparatively flat, there can be a conventional, large-scale impact cooling there.
  • the used cooling air causes in the absence of bypass current in addition to blocking the opening gap. For this purpose, the cooling air can flow from the second chamber through the holes in the partition into the first chamber.
  • a fastening device is arranged, which advantageously extends perpendicularly pointing away from the wall of the hot side.
  • the heat shield element is made of metal.
  • a heat shield element is realized as a cast component.
  • a generic annular combustion chamber comprising an outer shell and a number of heat shield elements, which are releasably secured to the interior of the outer shell facing the combustion chamber interior. Furthermore, the annular combustion chamber comprises a so-called Bypassplenum, extending over the circumference of the outer shell annular channel through which an air bypass flow is passed in the bypass mode.
  • the annular channel can be supplied via openings of the bypass air flow, wherein the annular channel has a combustion chamber interior facing annular gap through which the bypass air flow can be passed to the combustion chamber interior.
  • the annular channel and the annular gap can be performed circumferentially. If a fairly uniform distribution of the bypass air flow is ensured over the circumference, the annular channel and / or the annular gap can also be interrupted several times and thus consist of individual segment sections.
  • a novel annular combustion chamber is created by the use of a plurality of the above-described invention and / or heat shield elements advantageous for this purpose.
  • the heat shield elements are arranged such that the first chambers come to rest on the annular gap. In this respect are on one side of the annular gap, the partition and on the other side of the annular gap of the third edge portion. This allows a particularly advantageous flow of the bypass air flow from the annular gap through the first chamber and through the opening gap in the individual heat shield elements.
  • the outer shell has openings for the impact cooling of the heat shield elements.
  • openings for the impingement cooling of the first wall section are arranged in the first chamber in the annular channel of the outer shell and tubes in these openings are arranged, which extend to the hot side over the outer shell out into the first chambers.
  • cooling air can be directed to the first wall section of the first chamber.
  • this area is both convective, as well as cooled by impact cooling.
  • the heat shield element rests at least in sections with the free end on the outer shell. Due to the support, a transverse flow between the free end and the outer shell is largely prevented. Obviously, it is particularly advantageous if the support is provided on the peripheral edge and along the partition wall on the outer shell.
  • a sealing means between the free end of the heat shield element and the outer shell is provided.
  • the sealant is not present in sections, but circumferentially.
  • the sealing means is made of an elastic material, so that despite slight deviation in the shape of the free end and / or the outer shell as well as in vibrations a reliable tightness is achieved. For secure fixation of the sealant this is installed in the peripheral edge or in the partition and is beyond the free end.
  • first variant and the second variant is combined for sealing by sections an immediate support of the free end is provided on the outer shell and sections, especially in areas with higher pressure difference, a sealant between the free end and the Outer shell is present.
  • the object directed to a gas turbine plant is achieved by a gas turbine plant having an annular combustion chamber according to the invention.
  • FIGS. 1 to 4 show schematically and by way of example a metallic heat shield element 1 according to the invention, with a wall 3, which has a hot medium acted upon by a hot side 4 and a hot side 4 opposite cold side 5.
  • the FIGS. 1 to 3 show the cold side 5 and the FIG. 4 shows the hot side 4.
  • Adjacent to the wall 3 is an encircling edge 6 extending beyond the plane of the cold side 5 and having a free end 7 remote from the cold side 5.
  • the rim comprises Here, the two first opposite edge portion 56 and a transversely to the first edge portions 56 extending second edge portion 57 and a 57 opposite thereto third edge portion 58.
  • a partition 8 extends from the cold side 5 of the wall 3 to the height of the free end 7 between two opposite, formed by the edge 6 sides 9, so that on the cold side 5 of the wall 3 two separate first and second chambers 10, 11 are formed and the first chamber 10 has an opening gap 12 from the cold side 5 to the hot side 4, which is connects directly to the partition wall 8 and extends along the entire partition 8.
  • the wall 3 is divided into two sections, namely once into a first wall section 51 and a second wall section 52.
  • the partition 8 is inclined to the opening gap 12 and has a plurality of bores 13, whose axes 14 are directed to the surface of the cold side 5 in the first chamber 10.
  • a fastening device 15 is arranged, which extends substantially perpendicularly from the wall 3 away.
  • An assembly of the heat shield element 1 takes place, for example, via a plate spring assembly connected to the fastening device 15.
  • FIGS. 5 and 6 show a section through an annular combustion chamber 2 with a number of heat shield elements 1 according to the invention. Based on FIG. 5 the bypass concept should be explained.
  • the annular combustion chamber 2 of FIG. 5 comprises an outer shell 16, a number of heat shield elements 1 according to the invention, which are detachably secured to the inside of the outer shell 16, and a designated as Bypassplenum, extending over the circumference of the outer shell 16 annular channel 17 through which in the bypass mode, an air By-pass current is passed, with an annular gap 18 to the combustion chamber interior 19 out.
  • the heat shield elements 1 are now arranged such that their first chambers 10 are located on the annular gap 18 come.
  • the combustion chamber 2 upstream of the metallic heat shield elements 1 comprises a plurality of rows of ceramic heat shield elements 24, of which in the FIG. 5 only one is indicated, as well as downstream of the metallic heat shield elements 1 according to the invention, a number of further metallic heat shield elements 25, but without opening gaps 12th
  • FIG. 6 explains the cooling air management.
  • Bypass 26 passes from the annular channel 17 in the first chamber 10 of the heat shield elements 1 and passes through opening gaps 12 in the combustion chamber interior 19.
  • the outer shell 16 has first openings 20 for the impingement cooling 27 of the heat shield elements 1, in particular for the second chambers 11.
  • Natural die Bores 13 in the partition 8, the air used for baffle 27 of the second chamber 11 can continue to be used to block the opening gap 12 against hot gas from the combustion chamber interior 19 (see, sealing air 28).
  • second openings 21 for the impingement cooling 29 of the first chambers 10 are provided in the annular channel 17 of the outer shell 16.
  • tubes 22 are arranged, which extend into the first chambers 10. This arrangement serves for the impingement cooling 29 of the first chambers 10.
  • FIG. 7 shows a section of the annular combustion chamber 2 with heat shield elements 1 according to the invention, ceramic heat shield elements 24 and other metallic heat shield elements 25 in plan view.
  • FIG. 8 shows schematically and by way of example a gas turbine plant 23 according to the invention in a longitudinal section.
  • This comprises a compressor section 30, a combustion chamber section 31 and a turbine section 32.
  • a shaft 33 extends through all sections of the gas turbine installation 23.
  • the shaft 33 is provided with rings of compressor blades 34 and in the turbine section 32 Wreaths of turbine blades 35 equipped.
  • Wheels of compressor guide vanes 36 are located between the rotor blade rings in the compressor section 30 and wreaths of turbine guide vanes 37 in the turbine section 32.
  • the guide vanes extend from the housing 38 of the gas turbine installation 23 substantially in the radial direction to the shaft 33.
  • air 39 is drawn in through an air inlet 40 of the compressor section 30 and compressed by the compressor blades 34.
  • the compressed air is supplied to a combustion chamber 2 arranged in the combustion chamber 2, which is configured in the present embodiment as an annular combustion chamber 2.
  • a gaseous or liquid fuel is injected via at least one burner 42.
  • the resulting air-fuel mixture is ignited and burned in the combustion chamber 2.
  • the hot combustion exhaust gases flow from the combustor 2 into the turbine section 32, where they expand and cool, imparting momentum to the turbine blades 35.
  • the turbine guide vanes 37 serve as nozzles for optimizing the momentum transfer to the rotor blades 35.
  • the rotation of the shaft 33 caused by the momentum transfer is used to drive a load, for example an electric generator.
  • the expanded and cooled combustion gases are finally discharged through an outlet 44 from the gas turbine plant 23.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Elément (1) de bouclier thermique, notamment pour revêtir une chambre (2) de combustion, ayant une paroi (3) en une pièce ou en plusieurs pièces, qui (3) a un côté (4) chaud pouvant être soumis à un fluide chaud et un côté (5) froid opposé au côté (4) chaud, et comprenant un bord (6) voisin de la paroi (3), faisant tout le tour en s'éloignant du côté (4) chaud, et comprenant au moins deux premières parties (56) de bord opposées et une deuxième partie (57) de bord s'étendant transversalement aux premières parties de bord et une troisième partie (58) de bord opposée à la deuxième partie (57) de bord,
    caractérisé par
    une fente (12) d'ouverture, qui traverse la paroi (3) et qui subdivise la paroi (3) en une première partie (51) de paroi et en une deuxième partie (52) de paroi, et par une cloison (8), qui est disposée au voisinage de la fente (12) d'ouverture, qui se raccorde à la deuxième partie (52) de paroi et qui s'étend, en s'éloignant du côté chaud, entre les deux premières parties (56) de bord.
  2. Elément (1) de bouclier thermique suivant la revendication 1,
    caractérisé
    en ce que la fente (12) d'ouverture s'étend des deux côtés jusqu'aux premières parties (56) de bord.
  3. Elément (1) de bouclier thermique suivant la revendication 1 ou 2,
    caractérisé
    en ce que le bord (6) faisant le tour et la cloison (8) s'étendent jusqu'à une extrémité (7) libre.
  4. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 3,
    caractérisé
    en ce que la cloison (8) est inclinée au moins dans la région de la fente (12) d'ouverture.
  5. Elément (1) de bouclier thermique suivant la revendications 4,
    caractérisé
    en ce que la cloison (8) a plusieurs trous (13), dont (13) les axes (14) sont dirigés sur la première partie (52) de paroi.
  6. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 5,
    caractérisé
    en ce qu'au moins un dispositif (15) de fixation, s'étendant à partir du côté froid, est disposé sur la deuxième partie (51) de paroi.
  7. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 6,
    caractérisé
    en ce que l'élément (1) de bouclier thermique est en métal.
  8. Chambre de combustion (2) annulaire, comprenant une coque (16) extérieure, un certain nombre d'éléments (1) de bouclier thermique, qui (1) sont fixés de manière amovible à la face intérieure de la coque (16) extérieure et un conduit (17) annulaire, qui s'étend sur le pourtour de la coque (16) extérieure, auquel peut être apporté un courant d'air de dérivation et qui a une fente (18) annulaire ouverte vers l'intérieur (19) de la chambre de combustion, les éléments (1) de bouclier thermique étant disposés au voisinage de la fente (18) annulaire,
    caractérisée par des éléments (1) de bouclier thermique suivant l'une des revendications précédentes.
  9. Chambre de combustion annulaire suivant la revendication 8, caractérisée
    en ce que la fente (18) annulaire est disposée entre la cloison (8) et la troisième partie (57) de bord.
  10. Chambre de combustion (2) annulaire suivant la revendication 8 ou 9,
    caractérisée
    en ce que la coque (16) extérieure a des premières ouvertures (20) pour le refroidissement par rebondissement des éléments (1) de bouclier thermique.
  11. Chambre de combustion (2) annulaire suivant la revendication 10,
    caractérisée
    en ce que des deuxièmes ouvertures (21), pour le refroidissement par rebondissement de la première partie (52) de paroi, sont prévues dans la coque (16) extérieure et, dans celle-ci, sont disposés des tubes (22), qui, du côté chaud, dépassent de la coque (16) extérieure.
  12. Chambre de combustion (2) annulaire suivant l'une des revendications 8 à 11,
    caractérisée
    en ce que l'élément (1) de bouclier thermique s'applique, au moins par endroit, notamment en faisant le tour, par l'extrémité (7) libre sur la coque (16) extérieure et/ou en ce que, au moins par endroit, notamment en faisant le tour, il est disposé, entre l'extrémité libre de l'élément de bouclier thermique et la coque (16) extérieure, un agent d'étanchéité élastique et/ou incorporé au bord (6).
  13. Installation (23) de turbine à gaz, ayant une chambre de combustion (2) annulaire suivant l'une des revendications 8 à 12.
EP16713409.7A 2015-04-02 2016-03-30 Element de bouclier thermique avec contournement Not-in-force EP3132202B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015205975.8A DE102015205975A1 (de) 2015-04-02 2015-04-02 Umführungs-Hitzeschildelement
PCT/EP2016/056881 WO2016156370A1 (fr) 2015-04-02 2016-03-30 Élément de protection thermique par déviation

Publications (2)

Publication Number Publication Date
EP3132202A1 EP3132202A1 (fr) 2017-02-22
EP3132202B1 true EP3132202B1 (fr) 2018-09-19

Family

ID=55646578

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16713409.7A Not-in-force EP3132202B1 (fr) 2015-04-02 2016-03-30 Element de bouclier thermique avec contournement

Country Status (4)

Country Link
EP (1) EP3132202B1 (fr)
CN (1) CN107076418A (fr)
DE (1) DE102015205975A1 (fr)
WO (1) WO2016156370A1 (fr)

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Publication number Priority date Publication date Assignee Title
US11719438B2 (en) 2021-03-15 2023-08-08 General Electric Company Combustion liner

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EP3132202A1 (fr) 2017-02-22
CN107076418A (zh) 2017-08-18
DE102015205975A1 (de) 2016-10-06

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