EP1322838A1

EP1322838A1 - Moving blade for a turbo-machine and turbo-machine

Info

Publication number: EP1322838A1
Application number: EP01971957A
Authority: EP
Inventors: Volker Simon
Original assignee: Siemens AG
Current assignee: Siemens AG
Priority date: 2000-09-05
Filing date: 2001-08-23
Publication date: 2003-07-02
Anticipated expiration: 2021-08-23
Also published as: US20030185685A1; EP1186748A1; DE50111221D1; US6827556B2; CN1325761C; EP1322838B1; JP4499351B2; WO2002020948A1; JP2004508478A; EP1707745A2; CN1449470A; EP1707745A3

Abstract

The invention relates to a novel blade design which does not exceed the permitted stresses for particular loads, especially as a result of the centrifugal force and which at the same time, allows the turbo-machine (3) to function with a high degree of efficiency. To this end, an inventive moving blade (1) for a turbo-machine (3) consists at least partially of a cellular material (5), especially a foamed metal (21). Said cellular material (5) can be provided e.g. in the hollowed-out part (7) of the moving blade (1).

Description

description

Blade for a turbomachine and turbomachine

The invention relates to a rotor blade for a turbomachine. The invention further relates to a turbomachine with a rotor blade.

Rotor blades for turbomachines, for example rotor blades for high, medium or low pressure turbine parts of a steam turbine or gas turbine rotor blades for compressors or turbines, are usually made from homogeneous metallic alloys. In addition to milling processes, casting and forging techniques are also used. The metallic raw material is melted and then rolled as a bar material or forged as a blade blank.

Such a turbomachine comprises a single impeller or a number of impellers arranged one behind the other in the axial direction, the rotor blades of which are flowed around by a gaseous or vaporous flow medium during operation. The flow medium exerts a force on the blades, which causes a torque of the impeller or paddle wheel and thus the work performance. For this purpose, the rotor blades are usually arranged on a rotatable shaft of the turbomachine, the guide vanes of which are arranged on corresponding guide wheels on the stationary casing, the casing of the turbomachine surrounding the shaft, forming a flow channel.

While mechanical energy is supplied to the flow medium in the case of a compressor or a compressor, mechanical energy is withdrawn from the flow medium flowing through in a turbine as a flow machine. In a conventional turbomachine with a shaft rotating during operation and with the housing at rest, the centrifugal force in the or each rotating blade attached to the shaft has a tensile load which is superimposed on a bending load caused by the flow forces of the flow medium. This results in a critical load at those points in the blade root and in the shaft where the bending tensile stress and the tensile stress due to the centrifugal force overlap. Because of this critical load, the blade height is limited in its radial dimension and thus the efficiency of the turbomachine.

In particular, the blades of steam turbine low-pressure parts (LP blades) are mainly loaded by centrifugal force due to the rotation of the shaft. The load is therefore directly proportional to the density of the blade material used. Since the densities of the materials used are very similar to those of iron, the load on long LP blades is so great that a certain blade length cannot be exceeded. This is particularly important for the higher levels of LP blading, the radial dimensions of which are limited by the limits of the centrifugal force. Due to the limited blade length, only a certain outlet cross section for the flow medium can be achieved, so that the flow medium, e.g. the evaporation of a low-pressure turbine part leaves the turbomachine at high speed and consequently with high losses.

Previous solutions to problems for LP rotor blades provide that materials made of titanium alloys are used for very large blade lengths. Titanium alloys have a lower density than alloys based on iron, cobalt or nickel, and rotor blades made of this material are therefore subject to lower stresses than rotor blades made of the metallic materials hitherto customary, given the same dimensions. However, the disadvantage of this solution to the problem is that titanium alloys are very expensive and that the problem of centrifugal force still exists, albeit to a somewhat lesser extent. CO ω N> K_ι P ¹

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The rotor blade is preferably designed as a gas turbine rotor blade, a steam turbine rotor blade, in particular a low-pressure steam turbine rotor blade, or a compressor rotor blade. In particular, the use of the rotor blade in a low-pressure steam turbine appears to be particularly advantageous because, by using the cellular material, for example a metal foam, larger blade lengths with a lower centrifugal force load can be achieved compared to the conventional rotor blades. This has a direct, favorable effect on the efficiency of the turbomachine _/ for example a low-pressure steam turbine.

Which relates to a flow machine object is ^inventions' dung solved by a turbo-machine with a. Laufaufaufei according to the above statements.

The turbomachine is advantageously designed as a gas turbine, a steam turbine or a compressor.

The advantages of such a turbomachine arise in accordance with the statements on the rotor blade.

The invention is explained in more detail by way of example with reference to the drawing. They show schematically and partially simplified:

1 is a perspective view of a rotor blade for a turbomachine,

2 shows a perspective view of a rotor blade for a turbomachine which in some areas consists of a cellular material,

3 shows a perspective illustration of a rotor blade modified compared to FIG. 2, 4 shows a view of the rotor blade shown in FIG. 3 perpendicular to the plane along the section line IV-IV,

5 to 6 each show a sectional view of a rotor blade with a modified configuration compared to FIG. 4,

7 shows the detail in an enlarged view

VII of the rotor blade shown in FIG. 6, and

8 shows a greatly simplified longitudinal section of a

Detail of a turbomachine with moving blades.

The same reference symbols have the same meaning in the different figures.

^■ 1 shows in ^'perspective view of a rotor blade 1, extending along a longitudinal axis 25th The rotor blade has, in succession along the longitudinal axis, a fastening area 9, an adjoining blade platform 23 and an airfoil area 7. In the fastening area 9, a blade root 11 is formed, which serves to fasten the moving blade 1 to the shaft of a turbomachine (not shown in FIG. 1) (see FIG. 8). The blade root 11 is designed as a hammer head. Other configurations, for example as a fir tree or dovetail foot, are possible. In conventional blades 1, solid metallic materials are used in all areas 9, 23, 7 of the blade 1. The rotor blade 1 can be manufactured by a casting process, a forging process, a milling process or combinations thereof.

A blade 1 according to the invention is shown in FIG 2. Compared to the conventional rotor blade 1 shown in FIG. 1, the rotor blade 1 consists in some areas of a

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Claims

claims

1. rotor blade (1) for a turbomachine (3), which consists at least in regions of a cellular material (5).

2. Laufschaufei according to claim 1, with a cellular material (5) having the blade area (7).

3. Laufschaufei (1) according to claim 1 or 2, which has a fastening area (9), in particular a blade root (11), wherein the cellular material (5) is provided in the fastening area (9).

4. Laufschaufei (1) according to any one of claims 1, 2 or 3, wherein it has an inner region (13) and an inner region (13) surrounding the jacket region (15), in the jacket region (15) and / or in the inner region (13) the cellular material (5) is provided.

5. Laufschaufei (1) according to any one of the preceding claims, wherein the cellular material (5) forms an outer surface (39) with respect to the cells (17, 17A, 17B) closed structure.

6. Laufschaufei (1) according to any one of the preceding claims, wherein the cellular material (5) is a metal foam (21).

7. Blade (1) according to claim 6, wherein the density of the metal foam (21) is between about 5% to 50%, in particular between about 8% to 20%, of the density of the solid material (27).

8. Laufschaufei (1) according to claim 6 or 7, wherein the metal foam (21) made of a high temperature resistant material, in particular a nickel-based or cobalt-based alloy.

9. rotor blade (1) according to any one of the preceding claims, which is designed as a gas turbine blade, a steam turbine blade, in particular a low-pressure steam turbine blade, or a compressor blade.

10. Turbomachine (3) with a rotor blade (1) according to one of the preceding claims.

11. Turbomachine (3) according to claim 10, wherein it is designed as a gas turbine, a steam turbine (59), in particular a low-pressure steam turbine, or a compressor.

CHANGED REQUIREMENTS

[Received at the International Bureau on January 28, 2002 (January 20, 2002); original claims 1-11 replaced by amended claims 1-9 (2 pages)]

1. Laufschaufei (1) for a turbomachine (3), which at least partially from a cellular

Material (5) is made, the cellular material (5) forming an outer surface (39) with a closed structure with respect to cells (17, 17A, 17B).

2. Laufschaufei according to claim 1, with a the cellular material (5) having

Airfoil area (7).

4. Laufschaufei (1) according to any one of the preceding claims, wherein the cellular material (5) is a metal foam (21).

5. Laufschaufei (1) according to claim 4, wherein the density of the metal foam (21) between about 5% to 50%, in particular between about 8% to 20%, the density of the solid material (27).

6. Laufschaufei (1) according to claim 4 or 5, wherein the metal foam (21) made of a high temperature resistant material, in particular a nickel-based or cobalt-based alloy.

7. rotor blade (1) according to one of the preceding claims, which is designed as a gas turbine blade, a steam turbine blade, in particular a low-pressure steam turbine blade, or a compressor blade.

8. fluid machine (3) with a Laufaufaufei (1) according to any one of the preceding claims.

9. turbomachine (3) according to claim 8, which is designed as a gas turbine, a steam turbine (59), in particular a low-pressure steam turbine, or a compressor.