FR2475113A1 - CERAMIC ROTOR FOR TURBINE - Google Patents
CERAMIC ROTOR FOR TURBINE Download PDFInfo
- Publication number
- FR2475113A1 FR2475113A1 FR8100789A FR8100789A FR2475113A1 FR 2475113 A1 FR2475113 A1 FR 2475113A1 FR 8100789 A FR8100789 A FR 8100789A FR 8100789 A FR8100789 A FR 8100789A FR 2475113 A1 FR2475113 A1 FR 2475113A1
- Authority
- FR
- France
- Prior art keywords
- ceramic
- rotor
- bandage
- blades
- hub
- 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
- 239000000919 ceramic Substances 0.000 title claims abstract description 32
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title abstract 2
- 239000002131 composite material Substances 0.000 claims abstract description 7
- 229910052581 Si3N4 Inorganic materials 0.000 claims description 5
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 claims description 5
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- 230000006835 compression Effects 0.000 abstract description 7
- 238000007906 compression Methods 0.000 abstract description 7
- 239000007789 gas Substances 0.000 description 14
- 229910000601 superalloy Inorganic materials 0.000 description 5
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 230000008485 antagonism Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229920000620 organic polymer Polymers 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
- F01D5/28—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
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L'INVENTION CONCERNE LES ROTORS CERAMIQUES POUR TURBINES A GAZ. ELLE SE RAPPORTE A UN ROTOR 10 AYANT UN MOYEU 12 DESTINE A ETRE MONTE SUR UN ARBRE 26. UNE ROUE CERAMIQUE 14 A UNE RANGEE INTERNE D'AUBES 16, UN BANDAGE MEDIAN 20, UNE RANGEE EXTERNE DE PALES 18 DE COMPRESSION ET UN BANDAGE EXTERNE 22. SELON L'INVENTION, UNE STRUCTURE COMPOSITE COMPRENANT DES FILAMENTS FORME UN ANNEAU 24 QUI MAINTIENT EN COMPRESSION LES ELEMENTS CERAMIQUES, MEME LORS DU FONCTIONNEMENT. APPLICATION AUX MOTEURS A TURBINE A GAZ.THE INVENTION CONCERNS CERAMIC ROTORS FOR GAS TURBINES. IT RELATES TO A ROTOR 10 HAVING A HUB 12 INTENDED TO BE MOUNTED ON A SHAFT 26. A CERAMIC WHEEL 14 HAS AN INTERNAL ROW OF BLADES 16, A MEDIAN BANDAGE 20, AN EXTERNAL ROW OF 18 COMPRESSION BLADES AND AN EXTERNAL BANDAGE 22. ACCORDING TO THE INVENTION, A COMPOSITE STRUCTURE INCLUDING FILAMENTS FORMS A RING 24 WHICH MAINTAINS THE CERAMIC ELEMENTS IN COMPRESSION EVEN DURING OPERATION. APPLICATION TO GAS TURBINE ENGINES.
Description
La présente invention concerne les céramiques ré-The present invention relates to ceramic ceramics
sistant aux températures élevées et ayant une grande ré- at high temperatures and having a great deal
sistance mécanique et plus précisément des rotors céramiques mechanical resistance and more specifically ceramic rotors
légers, résistants à température élevée et de grande résis- light, resistant to high temperature and high resistance
tance mécanique, destinés à des turbines à gaz. Les rendements nominaux des ensembles moteurs sont devenus l'une des caractéristiques les plus importantes pour la mise au point des ensembles moteurs modernes. Des études mechanical power, intended for gas turbines. Nominal efficiencies of motor assemblies have become one of the most important features in the development of modern motor assemblies. Studies
ont montré clairement que les rendements nominaux des tur- have clearly shown that the nominal yields of tur-
bines à gaz pouvaient être fortement accrus lorsque les produits de combustion pouvaient frapper une roue de turbine gas could be greatly increased when combustion products could strike a turbine wheel
à des températuresmaximales. Cependant, les gaz de combus- at maximum temperatures. However, the combustion gases
tion nécessaires à l'obtention du rendement maximal dans les turbines à gaz ont une température de l'ordre de 13700C qui est bien supérieure aux limites fixées aux températures de fonctionnement des superalliages actuellement connus. On a déterminé que, si l'on devait utiliser les superalliages, non seulement on rencontrerait un problème de poids mais encore l'ensemble devrait comprendre des circuits complexes The requirements for obtaining the maximum efficiency in gas turbines have a temperature of the order of 137 ° C. which is well above the limits set at the operating temperatures of the superalloys currently known. It was determined that if superalloys were to be used, not only would there be a weight problem, but the whole should also include complex circuits
de refroidissement. Ce refroidissement permettrait l'uti- cooling. This cooling would allow the use
lisatior de ces superalliages; cependant, la température lisatior of these superalloys; however, the temperature
plus faible réduirait le rendement global de l'ensemble. lower would reduce the overall performance of the whole.
On s'est rendu compte qu'une solution plus com- We realized that a more com-
mode en pratique de ce problème d'antagonisme entre la mode in practice of this problem of antagonism between the
température et le rendement serait l'utilisation de cé- temperature and yield would be the use of
ramiques capables de supporter des températures élevées. which can withstand high temperatures.
Cependant, contrairement aux superalliages, les cérami- However, unlike superalloys, ceramics
ques sont extrêmement fragiles et cette propriété a rendu jusqu'à présent leur utilisation presqu'impossible dans les cas d'application de contraintes élevées. Comme les matières céramiques n'ont que des résistances modérées à These properties are extremely fragile and this property has hitherto rendered their use almost impossible in the case of the application of high stresses. Since ceramic materials have only moderate resistance to
la traction et sont très sensibles à tous les défauts lors- traction and are very sensitive to any faults
qubn les utilise de cette manière, par exemple comme ailet- used in this way, for example as a aiding-
tes d'un rotor d'une roue rotative de turbine, tout défaut de la structure provoque une destruction de l'ailette du rotor céramique ainsi qu'une destruction finale du rotor lui-même. Contrairement à cette faible résistance à la traction, la résistance à la compression des céramiques est With a rotor of a rotating turbine wheel, any defect in the structure causes a destruction of the ceramic rotor blade and a final destruction of the rotor itself. In contrast to this low tensile strength, the compressive strength of ceramics is
de l'ordre de 10 fois la résistance présentée à la traction. on the order of 10 times the resistance presented to the traction.
En conséquence, il semble souhaitable de maintenir les élé- Consequently, it seems desirable to maintain the
menrs céramiques d'un rotor de turbine sous compression et non pas sous tension pendant le cycle d'utilisation de la turbine. L'invention concerne un rotor axial céramique ceramic rims of a turbine rotor under compression and not under tension during the cycle of use of the turbine. The invention relates to a ceramic axial rotor
pour turbine à gaz qui comporte un moyeu métallique ou cé- for a gas turbine which has a metal hub or
ramique fixé à une roue comprenant une rangée interne d'aubes de turbine de détente et une rangée externe de pales de compression d'air, séparées l'une de l'autre par un bandage intermédiaire. Les pales du compresseur d'air ont aussi un bandage externe. Un filament ayant une rotor assembly attached to a wheel comprising an inner row of expansion turbine blades and an outer row of air compression blades, separated from each other by an intermediate bandage. The blades of the air compressor also have an external bandage. A filament having a
structure composite possédant un rapport élevé de la résis- composite structure with a high ratio of
tance mécanique à la masse, comprenant un filament de modu- mechanical strength, comprising a modulus filament
le élevé imprégné d'un polymère résistant à température the high impregnated with a temperature resistant polymer
élevée, est enroulé autour du bord extérieur de l'ensemble. high, is wrapped around the outer edge of the set.
L'invention concerne donc un rotor céramique pour The invention therefore relates to a ceramic rotor for
turbine à gaz, capable de maintenir tous les éléments céra- gas turbine, able to maintain all the ceramic elements
miques en compression lors du fonctionnement. in compression during operation.
Elle concerne aussi un rotor de turbine à gaz It also relates to a gas turbine rotor
capable de supporter des températures élevées. able to withstand high temperatures.
Elle concerne aussi un rotor céramique pour tur- It also relates to a ceramic rotor for tur-
bine à gaz qui a un faible poids.gas-powered machine that has a low weight.
Elle concerne aussi un tel rotor qui possède une It also concerns such a rotor which has a
résistance mécanique élevée.high mechanical strength.
D'autres caractéristiques et avantages de l'inven- Other features and advantages of the invention
tion ressortiront mieux de la description qui va suivre, fai- tion will be better described in the following description,
te en référence aux dessins annexés sur lesquels refer to the accompanying drawings in which
- la figure 1 est une perspective du rotor céra- FIG. 1 is a perspective view of the ceramic rotor
mique de turbine à gazgas turbine
- la figure 2a est une vue en plan du rotor c - FIG. 2a is a plan view of the rotor c.
ramique pour turbine à gaz de la figure l; - la figure 2b est une coupe partielle suivant la ligne 2b-2b de la figure 2a; - la figure 3 est une perspective d'un élément du rotor céramique pour turbine à gaz selon l'invention;et - la figure 4 est une coupe schématique illustrant ramique for a gas turbine of FIG. - Figure 2b is a partial section along the line 2b-2b of Figure 2a; FIG. 3 is a perspective view of an element of the ceramic gas turbine rotor according to the invention; and FIG. 4 is a diagrammatic section illustrating FIG.
un cycle de fonctionnement d'une turbine à gaz. a cycle of operation of a gas turbine.
Les figures 1 à 2b représentent un rotor axial céramique pour turbine à gaz, portant la référence 10 et formé de nitrure de silicium, de carbure de silicium, de "Sialon" ou d'une céramique analogue ayant une résistance mécanique élevée. Le rotor 10 comprend normalement un moyeu céramique ou métallique 12 fixé à une roue céramique 14. Cette dernière a en outre une rangée interne d'aubes 16 de turbine de détente et une rangée externe de pales 18 de compresseur d'air, séparées l'une de l'autre par un bandage médian 20. Les pales 18 du compresseur ont aussi Figures 1 to 2b show a ceramic axial rotor for gas turbine, bearing the reference 10 and formed of silicon nitride, silicon carbide, "Sialon" or a similar ceramic having a high mechanical strength. The rotor 10 normally comprises a ceramic or metal hub 12 fixed to a ceramic wheel 14. The latter also has an inner row of expansion turbine blades 16 and an outer row of air compressor blades 18, separated from each other. one of the other by a median bandage 20. The compressor blades 18 also have
un bandage externe 22. Un filament ayant une structure com- an outer bandage 22. A filament having a composite structure
posite possédant un rapport élevé de la résistance mécanique posite having a high ratio of mechanical strength
à lamasse est enroulé sur le bord externe 23 du bandage ex- is wrapped around the outer edge 23 of the outer bandage
terne 22, cette structure comprenant un filament de module dull 22, this structure comprising a module filament
élevé imprégné d'un polymère résistant à température élevée. high impregnated with a high temperature resistant polymer.
La structure composite forme un anneau 24 contre lequel les éléments céramiques sont comprimés lors de la rotation du rotor. Il est essentiel à cet effet que les pales froides The composite structure forms a ring 24 against which the ceramic elements are compressed during rotation of the rotor. It is essential for this purpose that the cold blades
18 du compresseur d'air se trouvent à l'extérieur par rap- 18 of the air compressor are on the outside with
port à la partie chaude des aubes 16 de la turbine de dé- port to the hot part of the vanes 16 of the turbine of
tente étant donné que la partie formant compresseur d'air ne constitue qu'un étage de compression, dans le cycle du moteur à turbine à gaz et, en coopération avec l'air admis, forme une barrière thermique protégeant la structure de because the air compressor part is only a compression stage in the cycle of the gas turbine engine and, in cooperation with the intake air, forms a thermal barrier protecting the air compressor structure.
l'anneau 24 formé du filament enroulé contre les tempéra- the ring 24 formed of the filament wound against the temperatures
tures élevées de la partie de détente. high heights of the relaxation part.
Des structures composites contenant un filament Composite structures containing a filament
enroulé, mettant en oeuvre comme liant des polymères orga- wound, using organic polymers as binder
niques, ont une température maximale d'utilisation de 315*C environ. Les fuites provenant de la partie de détente, par le joint qui se trouve au niveau du bandage médian 20, ne provoquent pas une rupture du rotor 10 mais seulement une légère augmentation des températures de l'air introduit dans have a maximum operating temperature of approximately 315 ° C. The leaks from the expansion portion, through the seal at the center band 20, do not cause the rotor 10 to rupture, but only a slight increase in the air temperatures introduced into the rotor.
le brûleur.the burner.
Des matières céramiques de résistance mécanique élevée telles que le nitrure de silicium sont nécessaires pour l'utilisation des températures élevées d'admission de la turbine telles que 13700C, permettant une augmentation du rendement des moteurs à turbine à gaz. Un coefficient de dilatation thermique extrêmement faible, et la résis- tance mécanique élevée présentée par le nitrure de silicium sont aussi des propriétés essentielles pour la matière du rotor étant donné les gradients élevés de température dus Ceramic materials of high mechanical strength such as silicon nitride are required for the use of high turbine inlet temperatures such as 13700C, allowing for increased efficiency of gas turbine engines. An extremely low coefficient of thermal expansion, and the high mechanical strength exhibited by silicon nitride are also essential properties for the rotor material given the high temperature gradients due to
à cette conception.to this design.
Le rotor dans son ensemble peut être sous forme d'un rotor céramique monolithique 10 comme représenté sur The rotor as a whole may be in the form of a monolithic ceramic rotor 10 as shown in FIG.
la figure 1, autour duquel la structure composite convena- FIG. 1, around which the composite structure
ble est enroulée, et qui est fixé par un moyeu 12 à l'arbre ble is wound, and which is fixed by a hub 12 to the shaft
26 ou qui peut être monté à partir de tronçons céramiques- 26 or that can be mounted from ceramic sections-
en forme de tranches comme représenté sur la figure 3. Ces tronçons individuels sont mis sous forme d'une roue et le filament est enroulé sur le bandage externe. La partie in the form of slices as shown in Figure 3. These individual sections are shaped as a wheel and the filament is wound on the outer bandage. The part
centrale est maintenue en compression et est fixée à l'ar- central station is kept in compression and is fixed in
bre 26 par un moyeu 12 comme indiqué sur la figure 2b. La possibilité de la construction d'un tel rotor original à 26 by a hub 12 as shown in Figure 2b. The possibility of building such an original rotor to
partir d'éléments individuels, comme représenté sur-la fi- from individual elements, as shown on the bottom
gure 3, permet la réalisation de rotors céramiques 10 de plus grande dimension que ceux qui peuvent être fabriqués sous forme monolithique, étant donné l'état actuel de la FIG. 3 allows the production of ceramic rotors 10 of larger size than those which can be manufactured in monolithic form, given the current state of the art.
technologie dans le domaine céramique. En outre, les élé- technology in the ceramic field. In addition,
ments céramiques plus petits peuvent être réalisés et éprouvés de façon moins coûteuse et à un moindrerisque smaller ceramic elements can be made and tested cheaper and to a lesser extent
qu'un élément monolithique de grande dimension. as a monolithic element of great size.
Le rotor selon l'invention non seulement peut The rotor according to the invention not only
supporter des températures élevées mais est encore extrê- withstand high temperatures but is still extremely
mement léger. Le nitrure de silicium, le carbure de sili- lightly. Silicon nitride, silicon carbide
cium, le "Sialon", etc. ont une masse volumique d'environ 3,0 à 3,8 g/cm3, par rapport à celle d'environ 8 g/cm3 cium, the "Sialon", etc. have a density of about 3.0 to 3.8 g / cm 3, compared to about 8 g / cm 3
d'un superalliage classique.a classic superalloy.
La figure 4 représente un exemple de cycle d'un Figure 4 shows an example of a cycle of a
moteur à turbine à gaz, correspondant à une disposition- gas turbine engine corresponding to a
possible des principaux éléments.possible of the main elements.
Claims (4)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11829580A | 1980-02-04 | 1980-02-04 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR2475113A1 true FR2475113A1 (en) | 1981-08-07 |
| FR2475113B1 FR2475113B1 (en) | 1985-03-22 |
Family
ID=22377719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR8100789A Granted FR2475113A1 (en) | 1980-02-04 | 1981-01-16 | CERAMIC ROTOR FOR TURBINE |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JPS56124603A (en) |
| DE (1) | DE3103821C2 (en) |
| ES (1) | ES8204058A1 (en) |
| FR (1) | FR2475113A1 (en) |
| GB (1) | GB2069065A (en) |
| IT (1) | IT1142247B (en) |
| SE (1) | SE8100355L (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2951226A1 (en) * | 2009-10-14 | 2011-04-15 | Turbomeca | AIR FILTERING DEVICE INTO INTERNAL COMBUSTION ENGINE INPUT WITH VENTILATION MEANS |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4580943A (en) * | 1980-12-29 | 1986-04-08 | The United States Of America As Represented By The Secretary Of The Army | Turbine wheel for hot gas turbine engine |
| GB2161110B (en) * | 1984-07-07 | 1988-03-23 | Rolls Royce | An annular bladed member having an integral shroud and a method of manufacture thereof |
| GB2164098B (en) * | 1984-09-07 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for turbine engines |
| DE3508889C1 (en) * | 1985-03-13 | 1992-02-20 | Alpine Ag, 8900 Augsburg | Air classifier with wear-free classifying wheel |
| FR2613772B1 (en) * | 1987-04-13 | 1991-06-28 | Gros Jean Marc | COMPRESSOR, MONOBLOCK TURBINE WHEEL. RECTIFIER, MONOBLOCK DISTRIBUTOR. AIR INLET, MONOBLOCK EXHAUST NOZZLE |
| US8011877B2 (en) * | 2008-11-24 | 2011-09-06 | General Electric Company | Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades |
| DE102009012749B4 (en) * | 2009-03-12 | 2012-08-30 | Siemens Aktiengesellschaft | Power amplifier with fiber composite |
| CN103975141A (en) * | 2011-09-23 | 2014-08-06 | 索克普拉科学与工程公司 | Rotor assembly having a concentric arrangement of a turbine portion, a cooling channel and a reinforcement wall |
| FR3005690B1 (en) * | 2013-05-16 | 2018-07-06 | Gerard Cerdan | COMPRESSOR TURBOREACTOR AND MONOBLOCS TURBINE (TR A CTM) |
| US11208893B2 (en) | 2015-05-25 | 2021-12-28 | Socpra Sciences Et Genie S.E.C. | High temperature ceramic rotary turbomachinery |
| GB201616239D0 (en) * | 2016-09-23 | 2016-11-09 | Intelligent Power Generation Limited | Axial Turbine |
| CA3044942A1 (en) * | 2016-11-25 | 2018-05-31 | Societe De Commercialisation Des Produits De La Recherche Appliquee Socpra Sciences Et Genie S.E.C. | High temperature ceramic rotary turbomachinery |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3042366A (en) * | 1958-05-05 | 1962-07-03 | Holmquist Ernst Rudolf Magnus | Axial flow gas turbine |
| DE1919310A1 (en) * | 1968-04-11 | 1969-10-23 | Aerostatic Ltd | Turbine rotor |
| GB1411316A (en) * | 1972-10-23 | 1975-10-22 | Fiat Spa | Vaned rotors for gas turbines |
| US4017209A (en) * | 1975-12-15 | 1977-04-12 | United Technologies Corporation | Turbine rotor construction |
| GB1473866A (en) * | 1973-05-22 | 1977-05-18 | United Turbine Ab & Co | Gas turbine power plant |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2027861C3 (en) * | 1970-06-06 | 1973-12-06 | Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Disc-shaped impeller for high-speed axial turbines |
-
1981
- 1981-01-16 FR FR8100789A patent/FR2475113A1/en active Granted
- 1981-01-19 ES ES498630A patent/ES8204058A1/en not_active Expired
- 1981-01-22 SE SE8100355A patent/SE8100355L/en not_active Application Discontinuation
- 1981-01-28 IT IT47655/81A patent/IT1142247B/en active
- 1981-02-03 GB GB8103330A patent/GB2069065A/en not_active Withdrawn
- 1981-02-04 JP JP1449281A patent/JPS56124603A/en active Pending
- 1981-02-04 DE DE3103821A patent/DE3103821C2/en not_active Expired
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3042366A (en) * | 1958-05-05 | 1962-07-03 | Holmquist Ernst Rudolf Magnus | Axial flow gas turbine |
| DE1919310A1 (en) * | 1968-04-11 | 1969-10-23 | Aerostatic Ltd | Turbine rotor |
| GB1411316A (en) * | 1972-10-23 | 1975-10-22 | Fiat Spa | Vaned rotors for gas turbines |
| GB1473866A (en) * | 1973-05-22 | 1977-05-18 | United Turbine Ab & Co | Gas turbine power plant |
| US4017209A (en) * | 1975-12-15 | 1977-04-12 | United Technologies Corporation | Turbine rotor construction |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2951226A1 (en) * | 2009-10-14 | 2011-04-15 | Turbomeca | AIR FILTERING DEVICE INTO INTERNAL COMBUSTION ENGINE INPUT WITH VENTILATION MEANS |
Also Published As
| Publication number | Publication date |
|---|---|
| IT8147655A0 (en) | 1981-01-28 |
| GB2069065A (en) | 1981-08-19 |
| SE8100355L (en) | 1981-08-05 |
| DE3103821C2 (en) | 1985-04-04 |
| DE3103821A1 (en) | 1981-12-03 |
| IT1142247B (en) | 1986-10-08 |
| FR2475113B1 (en) | 1985-03-22 |
| ES498630A0 (en) | 1982-04-01 |
| JPS56124603A (en) | 1981-09-30 |
| ES8204058A1 (en) | 1982-04-01 |
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