TIP CLEARANCE CONTROL FOR TURBINE BLADES
First Claim
1. An arrangement for a gas turbine engine comprising:
- a. a turbine blade configured to rotate about an axis;
b. a casing radially outside the turbine blade;
c. a carrier segment mounted to the casing so as to define a first impingement space therebetween, the carrier segment being positioned radially outside the turbine blade and comprising;
i. a first impingement carrier wall adjacent to and radially inside of the first impingement space, the first impingement carrier wall including a first aperture;
ii. a main carrier wall radially inside of the first impingement carrier wall;
iii. a cooling chamber radially inside of the main carrier wall;
iv. an intermediate chamber radially between the cooling chamber and the first impingement space;
v. a second aperture configured to allow ingress of air into the intermediate chamber, and wherein the first aperture of the first impingement carrier wall is configured to allow ingress of the air into the first impingement space; and
vi. a third aperture configured to allow flow of the air from the first impingement space to the cooling chamber.
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Accused Products
Abstract
An arrangement for a gas turbine engine that includes a turbine blade configured to rotate about an axis, a casing radially outside of the turbine blade, and a carrier segment mounted to the casing so as to define a first impingement space therebetween. The carrier segment is positioned radially outside the turbine blade and includes a first impingement carrier wall, a main carrier wall, and a cooling chamber. The first impingement carrier wall is adjacent to and radially inside of the first impingement space, and the first impingement carrier wall includes a first aperture. The main carrier wall is radially inside of the first impingement carrier wall. The cooling chamber is radially inside of the main carrier wall. Additionally, an intermediate chamber is disposed radially between the cooling chamber and the first impingement space. A second aperture is configured to allow ingress of air into the intermediate chamber.
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Citations
12 Claims
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1. An arrangement for a gas turbine engine comprising:
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a. a turbine blade configured to rotate about an axis; b. a casing radially outside the turbine blade; c. a carrier segment mounted to the casing so as to define a first impingement space therebetween, the carrier segment being positioned radially outside the turbine blade and comprising; i. a first impingement carrier wall adjacent to and radially inside of the first impingement space, the first impingement carrier wall including a first aperture; ii. a main carrier wall radially inside of the first impingement carrier wall; iii. a cooling chamber radially inside of the main carrier wall; iv. an intermediate chamber radially between the cooling chamber and the first impingement space; v. a second aperture configured to allow ingress of air into the intermediate chamber, and wherein the first aperture of the first impingement carrier wall is configured to allow ingress of the air into the first impingement space; and vi. a third aperture configured to allow flow of the air from the first impingement space to the cooling chamber. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A method of controlling a temperature of a turbine casing of a gas turbine engine,
the engine including: -
a turbine blade configured to rotate about an axis; a casing radially outside the turbine blade; a carrier segment mounted to the casing so as to define a first impingement space therebetween, the carrier segment being positioned radially outside the turbine blade and including; a first impingement carrier wall adjacent to and radially inside of the first impingement space, the first impingement carrier wall including a first aperture, a main carrier wall radially inside of the first impingement carrier wall; a cooling chamber radially inside of the main carrier wall; and an intermediate chamber radially between the cooling chamber and the first impingement space; the method comprising; passing air from an air feed source to the intermediate chamber; passing the air from the intermediate chamber, through the first aperture in the first impingement carrier wall, and into the first impingement space so that the air impinges on the casing; and passing the air from the first impingement space into the cooling chamber. - View Dependent Claims (10, 11, 12)
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Specification