Rotary kinetic fluid motors or pumps – With lubricating – sealing – packing or bearing means having... – For shaft sealing – packing – lubricating or bearing means
Patent
1994-08-04
1996-01-09
Look, Edward K.
Rotary kinetic fluid motors or pumps
With lubricating, sealing, packing or bearing means having...
For shaft sealing, packing, lubricating or bearing means
415116, 60 3983, F01D 2512
Patent
active
054824311
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND AND SUMMARY OF THE INVENTION
The invention relates to an arrangement for supplying cooling air to a turbine casing, especially that of an aircraft gas turbine, and comprising at least two cooling-air pipes or ducts branching off from a compressor stage, one pipe opening into the wall space of the turbine casing and the other pipe extending through the wall space and opening into a mounting space for the turbine bearings.
An arrangement for supplying cooling air to a turbine casing and comprising a single cooling-air pipe is shown in U.S. Pat. No. 4,542,623. An arrangement with two cooling-air pipes according to the preamble of claim 1 herein constitutes close prior art, at least within our firm. Cooling-air pipes of this kind extend at least partly outside the turbine casing and may become damaged, for example, when the aircraft gas turbine is in operation. The object of the invention, therefore, is to provide means which always ensure at least an adequate cooling of the turbine casing, particularly the wall space and the space for the turbine bearings.
To this end, the second cooling-air pipe has at least one air overflow opening located in the wall space of the turbine casing. Other advantageous features are disclosed in the subclaims.
According to the invention, cooling air enters the wall space in the turbine casing not only through the first cooling-air pipe, which opens into the wall space, but also through the second cooling-air pipe, which is mainly for cooling the turbine bearings mounting spaced for which purpose it extends through the wall space. According to the invention, air overflow openings are formed in the second cooling-air pipe in the region of the wall space so that cooling air can flow out into the wall space. If, for example, there is a break in the first cooling-air pipe which opens into the wall space, cooling air can still enter the wall space through the second cooling-air pipe and the openings therein. If, however, the second pipe is broken and the first pipe is intact, cooling air can flow from the wall space through the overflow openings into the second pipe so that the mounting space for the turbine bearings in the turbine casing can still be supplied with cooling air. The air overflow opening or openings, which can for example be in the form of holes in the tubular second pipe, act as 3-way valves.
To obtain a uniform distribution of cooling air, and also for the purpose of redundancy, two cooling-air pipes of the first-mentioned kind and two cooling-air pipes of the second-mentioned kind can be distributed around the periphery of the turbine casing.
The above-mentioned advantages and other advantages of the invention will be clear from the accompanying drawing of a preferred embodiment.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a partial longitudinal sectional view of a turbine casing according to the invention in the region of a second cooling-air pipe which is intact;
FIG. 2 is a partial longitudinal sectional view of the turbine casing in the region of an intact first cooling-air pipe; and
FIG. 3 is a sectional view corresponding to FIG. 1 but with a cooling-air pipe broken.
DETAILED DESCRIPTION OF THE DRAWINGS
Cooling air is supplied through a first pipe 1 and a second pipe 2 to a wall space 3 and to a mounting space 4 for turbine bearings of an aircraft gas turbine casing. The two cooling-air pipes 1, 2 branch off from the fourth compressor stage of the associated aircraft gas turbine (not shown). The two pipes 1, 2 are of tubular form and extend partly outside the casing. The first pipe 1 opens into the wall space 3, whereas the second pipe 2 opens into the mounting space 4. The cooling system shown has to be extremely reliable, since the turbine casing itself, via its wall space 3, must be reliably cooled under all circumstances, and so must the turbine bearings which are disposed in the separate mounting space 4.
The cooling system is made reliable to the extent needed in that the second cooling-air pipe 2 has at least one air overflow opening--a
REFERENCES:
patent: 2584899 (1952-02-01), McLeod
patent: 3527053 (1970-09-01), Horn
patent: 3527054 (1970-09-01), Hemsworth
patent: 4034558 (1977-07-01), Korta et al.
patent: 4079587 (1978-03-01), Nordstrom et al.
patent: 4109864 (1978-08-01), Clayton
patent: 4156342 (1979-05-01), Korta et al.
patent: 4369016 (1983-01-01), Dennison
patent: 4542623 (1985-09-01), Hovan et al.
patent: 4645415 (1987-02-01), Hovan et al.
patent: 4709545 (1987-12-01), Stevens et al.
patent: 5134844 (1992-08-01), Lee et al.
Bayerische Motoren Werke AG
Larson James A.
Look Edward K.
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