Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...
Reexamination Certificate
1999-02-23
2001-02-20
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...
C416S09600A, C415S115000
Reexamination Certificate
active
06190130
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a gas turbine moving blade platform constructed so as to enhance a cooling performance thereof.
2. Description of the Prior Art
FIG. 6
is a cross sectional view of a representative prior art gas turbine moving blade platform, which is an example of that used for a first stage moving blade. In
FIG. 6
, numeral
50
designates a platform in its entire form and numeral
51
designates a first stage moving blade. Numeral
52
designates a leading edge passage of the moving blade
51
and cooling passages
53
,
54
are in communication with the leading edge passage
52
and extend toward respective side portions of the platform
50
. The cooling passages
53
,
54
connect to cooling passages
55
,
56
, respectively, on both side portions and the cooling passages
55
,
56
open at a rear end of the platform
50
so that cooling air
70
flows out at the rear end of the platform.
In a front portion of the platform
50
, there are provided cooling passages
57
and
58
,
59
and
60
, respectively, on both sides thereof and these cooling passages
57
to
60
are bored at an angle from a lower surface toward an upper surface of the platform
50
to open at the upper surface so that cooling air is blown therefrom. Also, in a rear portion of the platform
50
, there are bored cooling passages
61
,
62
,
63
which also extend at an angle from the lower surface toward the upper surface of the platform
50
to open at the rear end thereof so that the cooling air is blown therefrom.
Further, in a central portion of the platform
50
, there are provided cooling passages
64
,
65
,
66
,
67
,
68
and these cooling passages are also bored at an angle from the lower surface toward the upper surface of the platform
50
so that the cooling air is blown from the upper surface, wherein an outlet end portion of each of the cooling passages
64
to
68
is enlarged in a funnel-like shape so that the cooling air is diffused on the upper surface.
FIG. 7
is a cross sectional view taken on line C—C of
FIG. 6
, wherein the cooling passages
55
,
56
are provided in both side portions of the platform
50
and the cooling passage
67
is bored at an angle from the lower surface toward the upper surface of the platform
50
.
FIG. 8
is a cross sectional view taken on line D—D of
FIG. 6
, wherein there are provided the cooling passage
55
extending from the front portion toward the rear portion of the platform
50
to open at the rear end and the inclined cooling passages
57
,
64
to
68
extending so that the cooling air is blown therethrough rearwardly and upwardly, respectively.
In the platform
50
constructed as above, cooling air which has been supplied into the moving blade
51
through the leading edge passage
52
flows portionally into the cooling passages
55
,
56
for cooling both side portions of the platform
50
and to then flow out of the rear end of the platform
50
. Also, the cooling passages
57
to
60
, and
61
to
63
, respectively, are provided in the front and rear portions of the platform
50
so that cooling air is introduced thereinto from the lower surface of the platform
50
to flow out of the upper surface of the front and rear end portions of the platform
50
. Further, the cooling passages
64
to
68
are provided in the central portion and cooling air flows therethrough from the lower surface of the platform
50
so as to flow out of the upper surface thereof. Thus, the entire portion of the platform
50
is cooled by the cooling air flowing therein and flowing out thereof.
In the representative prior art gas turbine moving blade platform as described above, there are provided cooling passages
55
,
56
which are main cooling passages extending linearly and in addition thereto, there are provided the multiplicity of cooling passages
57
to
60
,
61
to
63
, etc., which pass through the platform
50
at an angle and thus constitute comparatively long inclined routes. Hence, in the platform
50
, there are provided many such cooling air supply passages and thus processing of the platform itself becomes complicated and such a cooling structure for the platform is desired which can be made simpler and still has an excellent cooling effect to cool uniformly the entire portion of the platform including peripheral side portions thereof where there is a severe thermal influence.
SUMMARY OF THE INVENTION
It is therefore an object of the present invention to provide a gas turbine moving blade platform in which supply passages and flow passages of the platform cooling air are simplified so that processing of the platform is facilitated as well as cooling effect of the entire portion of the platform is maintained without being aggravated and especially the platform peripheral side portions are cooled effectively.
In order to achieve said object, the present invention provides the following:
(1) A gas turbine moving blade platform characterized in comprising two cooling passages, each being provided in said platform on each side of the moving blade, communicating at its one end with a leading edge passage of the moving blade and having at its the other end an opening at a side end surface of said platform; a cover for closing said opening of each of said two cooling passages; a side end portion cooling passage, being provided in each side end portion of said platform, communicating at its one end with each of said two cooling passages and having at its the other end an opening at a rear end surface of said platform; and a plurality of cooling holes, each communicating at its one end with any one of said side end portion cooling passages and having at its the other end an opening at the side end surface of said platform.
(2) A gas turbine moving blade platform characterized in comprising a plurality of cooling passages provided in said platform on each side of the moving blade between a leading edge portion and a trailing edge portion of the moving blade, each of said plurality of cooling passages being formed linearly toward a side end surface of said platform and arranged in parallel with each other so as to communicate at its one end with a cooling passage in the moving blade and open at its the other end at the side end surface of said platform.
(3) A gas turbine moving blade platform characterized in comprising a side portion cavity, which forms a cooling passage being provided recessedly in an inner side of said platform on each side of a base portion of the moving blade and extending between a front portion and a rear portion of said platform, said cooling passage being formed snake-wise and opening at a rear end surface of said platform; an inflow side cavity being formed recessedly in an inner side of the front portion of said platform so as to communicate with said side portion cavity; an inflow port for introducing therethrough a cooling air into said inflow side cavity from the inner side of said platform; and a bottom plate for covering recessed opening portions of said inflow side cavity and said side portion cavity.
(4) A gas turbine moving blade platform as mentioned in (3) above, characterized in that said side portion cavity and said inflow side cavity are grooves having same width and said inflow port is a cooling passage in a leading edge portion of the moving blade.
In the platform of item (1) above, there are provided the side end portion cooling passages along both side end surfaces of the platform so that cooling air is introduced thereinto from the leading edge passage of the moving blade through the two cooling passages of the front portion of the platform for cooling of both side portions of the platform to then flow out of the openings at the rear end surface of the platform. Further, there are provided the plurality of cooling holes communicating with any one of the side end portion cooling passages, for example, the side end portion cooling passage on a dorsal side of the moving blade which is exposed to a high temperature combustion gas, and the
Akita Eiji
Fukue Ichiro
Suenaga Kiyoshi
Tomita Yasuoki
Look Edward K.
Mitsubishi Heavy Industries Ltd.
Wenderoth , Lind & Ponack, L.L.P.
Woo Richard
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