Rotary kinetic fluid motors or pumps – With passage in blade – vane – shaft or rotary distributor...
Patent
1997-09-08
1999-09-21
Lopez, F. Daniel
Rotary kinetic fluid motors or pumps
With passage in blade, vane, shaft or rotary distributor...
415114, 415116, 416 95, 416 96R, 416 96A, 416 97R, F01D 518
Patent
active
059544759
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a gas turbine stationary blade which enables cooling without a pressure drop of the cooling vapor by the use of a simple structure.
2. Description of the Prior Art
As a recent tendency of industrial gas turbine, a turbine inlet gas temperature is gradually increased to obtain a high output and high efficiency. The temperature is now anticipated to reach as high as 1,500.degree. C. Therefore, a gas turbine stationary blade is sometimes cooled by the use of vapor (steam), having a high cooling effect, which flows within the blade. One example of a prior art cooling structure for a gas turbine stationary blade by way of vapor cooling is shown in FIGS. 3 and 4. The cooling vapor, supplied from a cooling vapor inlet 5 of an outer shroud 3, (as shown by arrows) passes through an impingement plate 13 having a multitude of fine holes and then passes through an inward cooling passage 7 within a blade unit 2 to cool a blade face. Then, it enters a finned internal cooling passage 9 (provided within an inner shroud 4a) to cool the inner shroud 4a. Next, the cooling vapor passes through an outward cooling passage 8 within the blade unit 2 to be discharged outside of a cooling vapor outlet 6 of the outer shroud 3 and to be collected in its entire amount.
In the prior art gas turbine stationary blade employing vapor cooling (as shown in FIGS. 3 and 4), the inner shroud 4a, through which the cooling vapor flows from the inward cooling passage 7 within the blade unit 2 to the outward cooling passage 8, has a complicated cooling passage configuration. There is a difficulty in the art of manufacture thereof, which leads to a problem of high cost. Also, there is a problem of a large pressure drop of the cooling vapor when it passes through a narrow portion of the inner shroud 4a, which leads to lowering of gas turbine efficiency.
SUMMARY OF THE INVENTION
It is therefore an object of the present invention to provide a gas turbine stationary blade which is able to solve the problems in the prior art.
The present invention provides a gas turbine stationary blade which has a feature that an outer shroud and a blade unit are cooled by vapor and an inner shroud is cooled by air.
In the gas turbine stationary blade according to the present invention, the outer shroud and the blade unit are cooled by vapor and the inner shroud is cooled by air supplied from another system. Consequently cooling of the shroud and the blade unit can be done effectively. Further, the cooling vapor simply enters to flow through an inward cooling passage and turns to flow through an outward cooling passage without flowing within the inner shroud. Therefore, the cooling passages through which the vapor flows can be made in a simplified configuration, and the cooling of the blade unit and the outer shroud can be achieved with less pressure drop and with a simple return flow passage.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a longitudinal cross sectional view of a gas turbine stationary blade of one embodiment according to the present invention.
FIG. 2 is a cross sectional view taken on line A--A of the gas turbine stationary blade of FIG. 1.
FIG. 3 is a longitudinal cross sectional view of a prior art gas turbine stationary blade employing vapor cooling.
FIG. 4 is a cross sectional view taken on line B--B of the prior art gas turbine stationary blade of FIG. 3.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
One embodiment according to the present invention is described with reference to FIGS. 1 and 2. A vapor cooling structure of an outer shroud 3 and a blade unit 2 in the present embodiment is nearly the same as that in the prior art shown in FIGS. 3 and 4. A cooling vapor supplied into the outer shroud 3 from a cooling vapor inlet 5 cools the outer shroud 3 and the blade unit 2, as described herebelow. The cooling vapor is then discharged outside of a cooling vapor outlet 6 to be collected in its entire amount. A different point in the present invention, however,
REFERENCES:
patent: 4712979 (1987-12-01), Finger
patent: 5320483 (1994-06-01), Cunha et al.
patent: 5320485 (1994-06-01), Bourguignon et al.
patent: 5340274 (1994-08-01), Cunha et al.
Matsuura Masaaki
Suenaga Kiyoshi
Uematsu Kazuo
Lopez F. Daniel
Mitsubishi Jukogyo Kabushiki Kaisha
Nguyen Ninh
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