DE102020209579A1 - HIGH PRESSURE COMPRESSOR SECTION FOR A CYCLE MACHINE AND RELATIVE CYCLE MACHINE, AND METHOD FOR MANUFACTURING A COMPONENT FOR THE HIGH PRESSURE COMPRESSOR SECTION FROM A FIBER COMPOSITE - Google Patents

Abstract

The present invention relates to a turbomachine and a high-pressure compressor section for a turbomachine with a plurality of compressor rotors (2,3) which are arranged one behind the other in the axial direction of the high-pressure compressor section (1), the last component of the high-pressure compressor section in the direction of flow being designed as a cone-shaped cone rotor (5). and the cone rotor (5) is formed from a ceramic fiber composite material. The invention also relates to a corresponding manufacturing method.

Description

BACKGROUND OF THE INVENTION

FIELD OF THE INVENTION

The present invention relates to a high-pressure compressor section for a turbomachine, in particular for an aircraft engine, and a corresponding turbomachine and a method for producing a component for the high-pressure compressor section from a fiber composite material, in particular from a ceramic fiber composite material, preferably with a Si/SiC or SiC matrix and SiC - or C - fibers.

STATE OF THE ART

Ceramic fiber composite materials are of interest for applications in aircraft turbine construction due to their properties, such as low specific weight, high chemical stability (oxidation resistance, corrosion resistance), wear resistance, hardness, high temperature resistance as well as strength and impact strength. However, the use of components made of ceramic fiber composite materials, such as components made of silicon carbide - ceramic with reinforcing fibers also made of silicon carbide, in turbomachines and in particular aircraft engines, is opposed to the brittleness of ceramic materials, although applications of components made of ceramic fiber composite materials in turbomachines have already been proposed are.

For example, the Chinese document suggests CN 109650924A proposes a method for manufacturing a turbine rotor from a disk made of a silicon carbide fiber composite material which is manufactured integrally with a blade.

The Patent Application Publication DE 10 2008 055 676 A1 discloses a rotor disk for a rotor of a compressor, in which the disk body is made up of a plurality of spokes. To this end, it is proposed to produce this writing body with a multiplicity of spokes from a fiber-reinforced ceramic matrix composite material.

However, not all problems have yet been solved for the specific technical use of rotor disks or rotor blades, for example with regard to failure safety in the event of contact with foreign bodies or strong tensile loads.

The US Patent Application Publication US 2018 0 22369 3A 1 discloses a turbine outlet arrangement with an outlet cone made of a ceramic fiber composite material which, however, is only exposed to low mechanical loads.

DISCLOSURE OF THE INVENTION

OBJECT OF THE INVENTION

It is the object of the present invention for a high-pressure compressor of a turbomachine, such as a gas turbine or an aircraft engine, to enable an increase in the operating temperature in the area of the rotors subjected to high temperatures, in order to enable improved efficiency of the turbomachine. The corresponding rotors should be able to be operated reliably and be easy to manufacture.

TECHNICAL SOLUTION

This object is achieved by a high-pressure compressor section with the features of claim 1 and a turbomachine with the features of claim 9 and a method for producing a corresponding high-pressure compressor section or a turbomachine with the features of claim 10. Advantageous configurations are the subject matter of the dependent claims.

The invention proposes for a turbomachine, in particular for an aircraft engine, that in a high-pressure compressor section, the last component of the high-pressure compressor section in the direction of flow, which is designed as a cone-shaped cone rotor and is arranged adjacent to the combustion chamber, is made of a ceramic fiber composite material. In contrast to rotor blades or rotor disks with blades, the cone-shaped cone rotor with its cone shape has a shape that is particularly suitable for producing this component from a fiber-reinforced ceramic material or a ceramic fiber composite material. Although the cone-shaped cone rotor is located in the immediate vicinity of the combustion chamber and is therefore exposed to a high temperature load, the properties of ceramic fiber composite materials make it possible to produce the cone-shaped cone rotor from them, since the ceramic fiber composite materials have high temperature resistance and good creep resistance.

The ceramic fiber composite materials that are used for the production of the cone-shaped cone rotor can have a ceramic matrix based on oxide - ceramics or non - oxide - ceramics and fibers that are embedded in the ceramic matrix, which are also made of oxide - Ceramics or non-oxide - ceramics or carbon formed include. Within the scope of this disclosure, carbon fibers are likewise regarded as ceramic materials.

In particular, the ceramic fiber composite material used can have a matrix material that includes at least one element from the group that includes aluminum oxide, magnesium oxide, silicon carbide, aluminum nitride, silicon nitride, aluminum titanate, mullite, zirconium oxide or aluminum oxide reinforced with zirconium oxide. The fiber material of the ceramic fiber composite material can be formed from the same material as the matrix and can in particular be selected from the group comprising aluminum oxide, silicon carbide, aluminum nitride, silicon nitride, zirconium oxide or carbon.

The fibers of the ceramic fiber composite material can be coated fibers, in particular coated silicon carbide fibers, in which case the coating can include one or more elements from the group containing aluminum, boron, silicon, carbon and nitrogen.

The ceramic fiber composite material is preferably formed by silicon carbide reinforced with carbon fibers, by silicon carbide reinforced with silicon carbide fibers, which under certain circumstances can include additional silicon phases, or aluminum oxide reinforced with aluminum oxide fibers.

The ceramic fiber composite material or the cone-shaped conical rotor can have an anti-oxidation coating in order to be able to further increase the operating temperatures.

In particular, a cone-shaped cone rotor made of a ceramic fiber composite material can be used in a high-pressure compressor section that includes a so-called part-shaft construction, i.e. a shaft connection, in particular a non-positive shaft connection, which holds the compressor rotors of the high-pressure compressor section together and presses them together. With such a construction, the cone-shaped conical rotor is subjected to compressive stresses in the axial direction, which can be easily dissipated by the ceramic fiber composite material.

The high-pressure compressor section or the cone-shaped cone rotor can be equipped with at least one sensor that monitors the vibration behavior of the cone-shaped cone rotor in order to be able to determine whether the cone-shaped cone rotor is damaged so that appropriate countermeasures can be taken.

The cone-shaped cone rotor is a simple, rotationally symmetrical component that can be manufactured in a simple manner by known methods for producing components from ceramic fiber composite materials, using a linear or sheet-like fiber structure to wind, braid and/or weave and / or put in a mold so as to form the shape of the cone-shaped cone rotor. The corresponding fiber structure is surrounded and/or infiltrated with the matrix material or a precursor material in order to produce the cone-shaped cone rotor from a ceramic fiber composite material. The arrangement of the fibers in the cone-shaped cone rotor allows the cone-shaped cone rotor to be adapted to the mechanical loads occurring during operation of the high-pressure compressor section or the turbomachine.

character list

• 1 einen Querschnitt durch einen Teil eines Hochdruckkompressorabschnitts gemäß der Erfindung und eines Teils einer benachbarten Brennkammer eines Flugtriebwerks und in
• 2 einen Querschnitt durch einen Teil einer weiteren Ausführungsform eines konusförmigen Kegelrotors.

The accompanying drawings show, purely diagrammatically,

• 1 a cross-section through a part of a high-pressure compressor section according to the invention and a part of an adjacent combustor of an aircraft engine and in
• 2 a cross section through part of a further embodiment of a cone-shaped cone rotor.

EXEMPLARY EMBODIMENTS

Further advantages, characteristics and features of the present invention become apparent in the following detailed description of the exemplary embodiments. However, the invention is not limited to these exemplary embodiments.

The enclosed 1 shows a partial section along the longitudinal axis or axis of rotation of an aircraft engine with a partial representation of a high-pressure compressor section 1 according to the invention and a combustion chamber 6. Here, only one half of the aircraft engine is shown above the axis of symmetry of the rotationally symmetrical aircraft engine, with the axis of symmetry being shown in dashed lines and the central longitudinal axis of the rotary shaft or the longitudinal axis of the engine.

The high-pressure compressor section 1 comprises several arranged one behind the other in the axial direction along the longitudinal axis of the engine Rotor disks 2 with rotor blades 3, which have a non-positive shaft connection 7, a so-called tie - shaft construction, as for example in the EP 2 365 184 A2 is described, are pressed against each other and held together. Stator blades 4, so-called guide blades, are arranged between the individual rows of blades with the rotor blades 3 in order to direct the air flowing through to the rotor blades 3 in a suitable manner.

The last component of the high-pressure compressor section 1 in the axial direction in the direction of flow is formed by a cone-shaped cone rotor 5 which is arranged on the shaft via a clamping element 8 in order to form the non-positive shaft connection 7 . In addition, the cone-shaped cone rotor 5 is connected to the adjacent rotor disk 2 via the rotor connection 10 . Furthermore, the cone-shaped conical rotor 5 has a seal 9 with an abradable lining in order to seal against an adjacent component.

The cone-shaped cone rotor 5 is arranged as the last component of the high-pressure compressor section 1 adjacent to the combustion chamber 6 and is accordingly subjected to a high thermal load, as indicated by the arrows intended to represent the thermal load in the attached figure.

According to the invention, the cone-shaped conical rotor 5 is formed from a ceramic fiber composite material or a fiber-reinforced ceramic, such as a silicon carbide ceramic reinforced with silicon carbide fibers or a silicon carbide ceramic reinforced with carbon fibers. Such ceramic fiber composite materials have a high temperature resistance and also good toughness due to the arrangement of the fibers. They also have very good creep resistance, so that the cone-shaped cone rotor 5 meets the requirements for the cone-shaped cone rotor 5 with high rotational speeds and the associated centrifugal forces and high temperature loads due to the proximity to the combustion chamber.

Due to the advantageous use in a high-pressure compressor section 1, in which the rotor components are clamped together via a non-positive shaft connection 7, the cone-shaped conical rotor 5 is essentially loaded with compressive stresses in the axial direction, which are very well absorbed by the fiber-reinforced ceramic material or the ceramic fiber composite material can be included. In addition, the fibers of the ceramic fiber composite material can be arranged in a suitable manner in the cone-shaped conical rotor 5 in order to be able to absorb the mechanical loads in the best possible way. Due to the low coefficient of thermal expansion of ceramic fiber composite material, there are essentially no other thermal stresses apart from the mechanical loads caused by rotation.

The ceramic fiber composite materials can be used with the expected temperature loads in the range of 800° C. to 1000° C. essentially without protection against oxidation, although additional protection against oxidation can be applied to the cone-shaped conical rotor 5 .

The cone-shaped cone rotor 5 can be produced as a simply constructed, rotationally symmetrical component using known methods for the production of ceramic fiber composite materials, the fibers being wound, braided and/or woven accordingly as linear fiber structures, for example fiber strands, or flat fiber structures, for example braiding or structures can to obtain the desired shape of the cone-shaped cone rotor 5. In addition, the fibrous structure can also be introduced into appropriate molds in order to subsequently fill the interstices of the fibrous structure with matrix material and to envelop the fibrous structure with this in order to form the shape of the cone-shaped cone rotor 5 .

Since the ceramic fiber composite materials already have a high level of toughness due to the inclusion of the fibers, use in the high-pressure compressor section 1 is possible. In addition, for the cone-shaped cone rotor 5 as the last component of the high-pressure compressor section 1, there is a small risk that the component could be damaged by the action of a foreign body.

In addition, the high-pressure compressor section 1 can have at least one sensor for monitoring the vibration of the cone-shaped cone rotor 5 in order to detect possible damage to the component in good time.

the 2 shows similar to the 1 a partial sectional view of another embodiment of a cone-shaped cone rotor 5, which differs in its external shape from the embodiment of FIG 1 distinguishes to make it clear that the shape of the cone rotor 5 can be different. At the cone rotor 5 of 2 two abradable pads are attached to form seals 9 with adjacent components.

Although the present invention has been described in detail on the basis of the exemplary embodiment, it goes without saying for a person skilled in the art that the invention is not limited to this exemplary embodiment game is limited, but rather that modifications are possible in such a way that individual features can be omitted or other types of combinations of features can be realized without departing from the scope of protection of the appended claims. In particular, the present disclosure includes all combinations of the individual features described, so that individual features that are only described in connection with the exemplary embodiment can also be used in other exemplary embodiments or combinations of individual features that are not explicitly shown.

Reference List

1

high pressure compressor section

2

rotor disc

3

rotor blade

4

stator blade

5

conical cone rotor

6

combustion chamber

7

shaft connection

8th

deadlock

9

poetry

10

rotor connection

QUOTES INCLUDED IN DESCRIPTION

This list of the documents cited by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent Literature Cited

• CN 109650924A [0003]
• DE 102008055676 A1 [0004]
• US20180223693A [0006]
• EP 2365184 A2 [0021]

Claims (10)

High-pressure compressor section for a turbomachine with a plurality of compressor rotors (2,3) which are arranged one behind the other in the axial direction of the high-pressure compressor section (1), the last component of the high-pressure compressor section in the direction of flow being designed as a cone-shaped cone rotor (5), characterized in that s the cone rotor (5) is formed from a ceramic fiber composite material. High pressure compressor section after claim 1 , characterized in that s the ceramic fiber composite material comprises a ceramic matrix based on oxide ceramics or non-oxide ceramics and fibers of oxide ceramics or non-oxide ceramics or carbon embedded in the ceramic matrix. High pressure compressor section after claim 1 or 2 , characterized in that s the matrix material of the ceramic fiber composite material has at least one element from the group consisting of aluminum oxide, magnesium oxide, silicon carbide, aluminum nitride, silicon nitride, aluminum titanate, mullite, zirconium oxide or aluminum oxide reinforced with zirconium oxide, and that the fiber material of the ceramic fiber composite material has at least one element from the group comprising aluminum oxide, silicon carbide, aluminum nitride, silicon nitride, zirconium oxide or carbon. High-pressure compressor section according to one of the preceding claims, characterized in that the fibrous material comprises coated fibres, in particular coated SiC fibres, the coating comprising one or more elements from the group consisting of Al, B, Si, C and N. A high pressure compressor section as claimed in any one of the preceding claims characterized in that the ceramic fiber composite material includes an anti-oxidation coating. High-pressure compressor section according to one of the preceding claims, characterized in that the ceramic fiber composite material is selected from the group comprising C/SiC, SiC/SiC and Al ₂ O ₃ /Al ₂ O ₃ . A high pressure compressor section according to any one of the preceding claims, characterized in that the high pressure compressor section (1) comprises a shaft connection (7) which holds the compressor rotors (2,3,5) together so that the conical cone rotor (5) is subjected to compressive stresses. High-pressure compressor section according to one of the preceding claims, characterized in that the high-pressure compressor section (1) comprises at least one sensor with which the vibration behavior of the cone-shaped cone rotor (5) is monitored. Flow machine, in particular gas turbine or aircraft engine, with a high-pressure compressor section (1) according to one of the preceding claims. A method of manufacturing a high pressure compressor section according to any one of Claims 1 until 8th , in which the cone-shaped conical rotor (5) is produced from a linear or flat fiber structure, which is wound and/or braided and/or wound and/or placed in a mold and surrounded with the matrix material or a precursor material for this purpose and/or is infiltrated.

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