EP3781794A1 - Ensemble d'anneau de turbine avec etancheite inter-secteurs - Google Patents
Ensemble d'anneau de turbine avec etancheite inter-secteursInfo
- Publication number
- EP3781794A1 EP3781794A1 EP19722665.7A EP19722665A EP3781794A1 EP 3781794 A1 EP3781794 A1 EP 3781794A1 EP 19722665 A EP19722665 A EP 19722665A EP 3781794 A1 EP3781794 A1 EP 3781794A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- groove
- sealing
- ring
- downstream
- upstream
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 159
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 61
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 11
- 229910052759 nickel Inorganic materials 0.000 claims description 7
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 7
- 229910052721 tungsten Inorganic materials 0.000 claims description 7
- 239000010937 tungsten Substances 0.000 claims description 7
- 229910017052 cobalt Inorganic materials 0.000 claims description 6
- 239000010941 cobalt Substances 0.000 claims description 6
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 6
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 3
- 239000011159 matrix material Substances 0.000 claims description 3
- 229910010293 ceramic material Inorganic materials 0.000 claims description 2
- 210000002105 tongue Anatomy 0.000 description 101
- 238000001816 cooling Methods 0.000 description 21
- 239000007789 gas Substances 0.000 description 8
- 210000001503 joint Anatomy 0.000 description 8
- 210000003462 vein Anatomy 0.000 description 7
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 238000004088 simulation Methods 0.000 description 6
- 239000011153 ceramic matrix composite Substances 0.000 description 5
- 238000009423 ventilation Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 229920002134 Carboxymethyl cellulose Polymers 0.000 description 2
- 235000010948 carboxy methyl cellulose Nutrition 0.000 description 2
- 229920006184 cellulose methylcellulose Polymers 0.000 description 2
- 238000012710 chemistry, manufacturing and control Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 210000002310 elbow joint Anatomy 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000003870 refractory metal Substances 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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 opening or openings present in the second sealing tongue namely the tongue closest to the outer face of the platform of each ring sector which is intended to receive a cooling flow, allow the cooling flow to pass through this second sealing tongue and to impact the first sealing tongue, namely the tongue of sealing most exposed to heat flow. It is thus possible to cool the first sealing tongue which can then be exposed to flows of higher temperatures.
- the air flow used to impact the first sealing tongue also reloads the pressure in the area between the first and second sealing tabs. The risk of reintroduction of hot air from the vein in this zone is thus reduced.
- the opposite faces of the adjacent ring sectors and the sealing tongues are thus better protected from high temperature flows.
- a second angled sealing element housed in both the first groove and the downstream groove.
- a downstream sealing strip comprises first and second continuous portions forming an angle between them, the first portion extending in the downstream groove and the second portion extending partially in the first groove, the second portion of the second tongue; sealing strip overlapping the first portion of the downstream sealing tab, the second portion of said downstream sealing tab overlapping the first sealing tab.
- each of the sealing tongues is made of a metal alloy based on nickel, cobalt or tungsten.
- each opening in the second sealing tongue has an area of between 0.1 mm 2 and 10 mm 2 . According to a particular characteristic of the ring assembly of the invention, each opening in the second sealing tongue is entirely surrounded by the material of said second sealing tongue.
- Figs. 2A and 2B are partial schematic perspective views showing the positioning of sealing tabs in a ring sector of the turbine ring assembly of Fig. 1;
- the turbine ring 1 is formed of a plurality of adjacent ring sectors 10, FIG. 1 being a radial sectional view along a plane passing between two contiguous ring sectors.
- the arrow DA indicates the axial direction with respect to the turbine ring 1 while the arrow DR indicates the radial direction with respect to the turbine ring 1.
- each sealing tongue is housed in grooves facing each other in the opposite edges of two neighboring ring sectors.
- each ring sector 10 comprises a first groove 41 which here extends horizontally in the redefinel2 in the vicinity of the inner face 12a thereof and in which is housed the first sealing tongue 21, a second groove 40 which extends here horizontally in the redefinel2 in the vicinity of the outer face 12b thereof and above the groove 41 in the radial direction DR, in which is housed the second sealing tongue 20, a groove upstream 42 formed in the upstream lug 14 in which is housed the upstream sealing tongue 22 and a downstream groove 43 formed in the downstream leg 16 and in which is housed the downstream sealing tongue 23.
- FIGS. 1, 2A and 2B illustrate a single ring sector 10 in which the tongues 20, 21, 22 and 23 are partially inserted respectively in the grooves 40, 41, 42 and 43.
- the portion of the tongues 20, 21, 22 and 23 protruding from ring sector 10 are introduced into corresponding grooves in the neighboring ring sector (not shown in FIGS. 1, 2A and 2B).
- Fig. 3 shows a turbine ring assembly according to another embodiment of the invention.
- the metal ring support structure 3 and the ring sectors 10 forming the turbine ring 1, here made of ceramic matrix composite material (CMC), are identical to those already described above. before in connection with Figures 1, 2A and 2B and will not be described here again for the sake of simplification.
- CMC ceramic matrix composite material
- each sealing tongue is housed in grooves facing each other in the opposite edges of two neighboring ring sectors.
- each ring sector 10 has a first groove 41 extending here horizontally in the redefinel2 in the vicinity of the inner face 12a thereof, a second groove 40 extending here horizontally in the redefinel2 in the vicinity of the outer face 12b thereof and above the groove 41 in the radial direction DR, an upstream groove 42 formed in the upstream leg 14 and a downstream groove 43 formed in the downstream leg.
- the second groove 40 opens on one side in the radially inner portion of the upstream groove 42 and on the other side in the radially inner portion of the downstream groove 43.
- the downstream groove 43 also opens into the first groove 41.
- the upstream sealing tongue 62 comprises first and second continuous portions 620 and 621 forming an angle therebetween, the first portion 620 extending into the upstream groove 42 and the second portion 621 partially extending into the second groove 40.
- the second sealing tongue 60 comprises first and second continuous portions 600 and 601 forming an angle therebetween, the first portion 600 extending into the second groove 40 and the second portion 601 extending partially into the downstream groove 23, the second portion 621 of the upstream sealing tongue 22 overlapping the first portion 600 of the second sealing tongue 20.
- the downstream sealing tongue 23 comprises first and second continuous portions 630 and 631 forming an angle between them, the first portion 630 extending into the downstream groove 43 and the second portion 631 extending partially into the first groove 41.
- the second portion Me portion 601 of the second sealing tab 20 overlaps the first portion 630 of the downstream sealing tab 23 while the second portion 631 of the downstream sealing tab 23 overlaps the first sealing tab 21.
- cooling flow FR is introduced through passages 35 present in the annular upstream radial flange 32 of the ring support structure 3, the flow cooling device imparting the outer surface 12b of the platform after it enters each ring sector 10.
- the cooling flow can be taken from the compressor stage or come from a flow of air bypassing the combustion chamber. Thanks to the presence of the openings 126 and 127 in the second tongue 60 which is located closer to the outer face 12b of the redefinel2 receiving the cooling stream FR, a fraction of the cooling stream FR can reach the first tab 61 and cool the latter. It is thus possible to increase the temperatures of the gases flowing in the vein on the side of the inner face 12a of the ring sector platform without the risk of damaging the most exposed heat-sealing tab, namely the first tongue 61.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1853302A FR3080142B1 (fr) | 2018-04-16 | 2018-04-16 | Ensemble d'anneau de turbine avec etancheite inter-secteurs |
PCT/FR2019/050797 WO2019202234A1 (fr) | 2018-04-16 | 2019-04-04 | Ensemble d'anneau de turbine avec etancheite inter-secteurs |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3781794A1 true EP3781794A1 (fr) | 2021-02-24 |
EP3781794B1 EP3781794B1 (fr) | 2022-07-20 |
Family
ID=62751119
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19722665.7A Active EP3781794B1 (fr) | 2018-04-16 | 2019-04-04 | Ensemble d'anneau de turbine avec étanchéité inter-secteurs |
Country Status (5)
Country | Link |
---|---|
US (1) | US11111823B2 (fr) |
EP (1) | EP3781794B1 (fr) |
CN (1) | CN112004993B (fr) |
FR (1) | FR3080142B1 (fr) |
WO (1) | WO2019202234A1 (fr) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20230304412A1 (en) * | 2022-01-28 | 2023-09-28 | Raytheon Technologies Corporation | Vane forward rail for gas turbine engine assembly |
US11773751B1 (en) | 2022-11-29 | 2023-10-03 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with pin-locating threaded insert |
US11840936B1 (en) | 2022-11-30 | 2023-12-12 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with pin-locating shim kit |
US11713694B1 (en) | 2022-11-30 | 2023-08-01 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with two-piece carrier |
US11732604B1 (en) | 2022-12-01 | 2023-08-22 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with integrated cooling passages |
US11885225B1 (en) | 2023-01-25 | 2024-01-30 | Rolls-Royce Corporation | Turbine blade track with ceramic matrix composite segments having attachment flange draft angles |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2869944B1 (fr) * | 2004-05-04 | 2006-08-11 | Snecma Moteurs Sa | Dispositif de refroidissement pour anneau fixe de turbine a gaz |
US8753073B2 (en) * | 2010-06-23 | 2014-06-17 | General Electric Company | Turbine shroud sealing apparatus |
US10316683B2 (en) * | 2014-04-16 | 2019-06-11 | United Technologies Corporation | Gas turbine engine blade outer air seal thermal control system |
US20160053633A1 (en) * | 2014-08-22 | 2016-02-25 | Rolls-Royce Corporation | Seal with cooling feature |
US9874104B2 (en) * | 2015-02-27 | 2018-01-23 | General Electric Company | Method and system for a ceramic matrix composite shroud hanger assembly |
FR3041993B1 (fr) * | 2015-10-05 | 2019-06-21 | Safran Aircraft Engines | Ensemble d'anneau de turbine avec maintien axial |
WO2018004583A1 (fr) * | 2016-06-30 | 2018-01-04 | Siemens Aktiengesellschaft | Ensemble aube de stator ayant un joint d'étanchéité à face d'accouplement comportant des trous de refroidissement |
FR3068071B1 (fr) * | 2017-06-26 | 2019-11-08 | Safran Aircraft Engines | Ensemble pour la liaison par palonnier entre un carter de turbine et un element annulaire de turbomachine |
-
2018
- 2018-04-16 FR FR1853302A patent/FR3080142B1/fr active Active
-
2019
- 2019-04-04 US US17/047,973 patent/US11111823B2/en active Active
- 2019-04-04 WO PCT/FR2019/050797 patent/WO2019202234A1/fr unknown
- 2019-04-04 CN CN201980025327.5A patent/CN112004993B/zh active Active
- 2019-04-04 EP EP19722665.7A patent/EP3781794B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
US20210164366A1 (en) | 2021-06-03 |
CN112004993A (zh) | 2020-11-27 |
FR3080142B1 (fr) | 2020-05-01 |
EP3781794B1 (fr) | 2022-07-20 |
WO2019202234A1 (fr) | 2019-10-24 |
CN112004993B (zh) | 2023-04-14 |
FR3080142A1 (fr) | 2019-10-18 |
US11111823B2 (en) | 2021-09-07 |
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