Turbomachine rotor blade and disk

Details Turbomachine rotor blade and disk Turbomachine rotor blade and disk

1999-11-26

2001-09-18

Look, Edward K. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

C416S239000, C416S248000

Reexamination Certificate

active

06290464

ABSTRACT:

REFERENCE TO OTHER APPLICATIONS
This application claims priority to German patent application no. 198 54 908.3 filed Nov. 27, 1998, which is incorporated by reference herein.
1. Field of the Invention
This invention relates to a blade of a turbomachine, more particularly of an axial-flow high-pressure turbine, having at least one integrated cooling air duct, which when viewed in the direction of flow of the working gas conducted by the blade, issues at the downstream back of the blade root. This invention also relates to a rotor disk of a turbomachine having several blades designed in accordance with the present invention. For related state of the art, reference is made to GB 2 057 573 A and DE 32 10 626 C2.
2. Description of the Prior Art
A blade of this description may find use in the high-pressure turbine of an aircraft gas turbine engine. An optimally designed cooling system of a high-performance aircraft engine then requires for each of its generally multiple turbine stages, especially high-pressure turbine stages, an optimized, i.e. minimized, flow of cooling air of a suitably adapted inlet temperature and feed pressure. The first high-pressure turbine stage, for example, obtains its cooling air from the final stage of a multiple-stage compressor, which in aircraft engines is arranged upstream of the high-pressure turbine, while the second high-pressure turbine stage obtains its cooling air from one of the final compressor stages, and a third turbine stage, if present, obtains its cooling air from one of the central compressor stages. An engine cooling system designed along these lines needs a complex cooling air ducting network flange-mounted to the compressor and turbine casings. Said design is however impaired by its heavy weight and susceptibility to breakdowns.
For cooling the turbine stages, especially high-pressure turbine stages, i.e. for cooling the associated blades and rotor disks, use can generally also be made of the internal cooling air flow of the turbomachine/gas turbine or aircraft engine, said flow normally being delivered by a single feed source of cooling air, i.e., by the final compressor stage, but this cooling air flow lacks adequate cooling capacity especially for the final high-pressure turbine stage of the multiple-stage high-pressure turbine, considering that said cooling air flow necessarily picks up heat in its passage along the preceding cooling air ducts. Said preceding cooling air ducts normally extend through the turbine rotor disk or the roots of the blades arranged on the rotor disk, as is shown in particular in the initially cited GB 2 057 573 A.
SUMMARY OF THE INVENTION
The object underlying the present invention is to provide a remedy for the problem described above. The solution of this problem is to provide an arrangement characterized in that the cooling air duct issuing at the back of the blade root branches off from a cooling air chamber provided in the blade root from which at least one cooling air duct issuing at the gas-wetted surface of the blade is provided with cooling air, and in that the cooling air duct issuing at the back of the blade root is designed to deflect the cooling air stream it carries while providing a substantially continuous passage.
Further objects and advantages of the present invention are cited in the subclaims by way of a turbomachine rotor disk having several blades in accordance with the present invention.


REFERENCES:
patent: 3791758 (1974-02-01), Jenkinson
patent: 4292008 (1981-09-01), Grosjean et al.
patent: 4425079 (1984-01-01), Speak et al.
patent: 4820116 (1989-04-01), Hovan et al.
patent: 5795130 (1998-08-01), Suenaga et al.
patent: 6022190 (2000-02-01), Schillinger
patent: 6071075 (2000-06-01), Tomita et al.
patent: 906636 (1954-03-01), None
patent: 3210626 (1982-11-01), None
patent: 3835932 (1990-04-01), None
patent: 19705442 (1998-08-01), None
patent: 2057573 (1979-08-01), None

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