Non-integral turbine blade platforms and systems
First Claim
Patent Images
1. A system, comprising:
- a first turbine blade platform, comprising;
a first exterior side contoured to interface with a first airfoil of a first turbine blade disposed at a first angular position; and
a second exterior side disposed generally opposite the first exterior side and contoured to interface with a second airfoil of a second turbine blade disposed at a second angular position, wherein the first turbine blade platform is configured to be held in place by respective contours of the first airfoil and the second airfoil and without directly fastening to a rotor wheel.
2 Assignments
0 Petitions
Accused Products
Abstract
In one embodiment, a turbine blade platform may be disposed between two turbine blades. The platform may include a first exterior side configured to interface with a first turbine blade. The platform also may include a second exterior side disposed generally opposite the first exterior side and configured to interface with a second turbine blade.
207 Citations
20 Claims
-
1. A system, comprising:
a first turbine blade platform, comprising; a first exterior side contoured to interface with a first airfoil of a first turbine blade disposed at a first angular position; and a second exterior side disposed generally opposite the first exterior side and contoured to interface with a second airfoil of a second turbine blade disposed at a second angular position, wherein the first turbine blade platform is configured to be held in place by respective contours of the first airfoil and the second airfoil and without directly fastening to a rotor wheel. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
-
9. A system, comprising:
-
a plurality of turbine blades circumferentially spaced about an axis; and at least one turbine blade platform disposed between, removably coupled to, and supported by first and second turbine blades of the plurality of turbine blades, wherein the at least one turbine blade platform is contoured to interface with respective airfoils of each of the first and second turbine blades, and wherein the at least one turbine blade platform is configured to be retained between the first and second turbine blades by respective contours formed in the first and second turbine blades and without directly fastening to a rotor wheel. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16)
-
-
17. A method, comprising:
-
positioning turbine blades into openings disposed circumferentially about a rotor wheel; positioning turbine blade platforms between each of the turbine blades;
the turbine blade platforms are separate from, and circumferentially between, the turbine blades;inserting the turbine blades into the rotor wheel to secure the turbine blades within the rotor wheel; and setting the turbine blade platforms towards the rotor wheel such that each of the turbine blade platforms interfaces with an adjacent turbine blade platform to encompass one of the turbine blades and each of the turbine blade platforms is held in place by respective contours formed in adjacent turbine blades and without directly fastening to the rotor wheel. - View Dependent Claims (18, 19, 20)
-
Specification