skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Hot gas path component having near wall cooling features

Abstract

A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.

Inventors:
; ;
Publication Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1410544
Patent Number(s):
9,828,915
Application Number:
14/739,849
Assignee:
General Electric Company (Schenectady, NY) NETL
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2015 Jun 15
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Miranda, Carlos Miguel, Kottilingam, Srikanth Chandrudu, and Lacy, Benjamin Paul. Hot gas path component having near wall cooling features. United States: N. p., 2017. Web.
Miranda, Carlos Miguel, Kottilingam, Srikanth Chandrudu, & Lacy, Benjamin Paul. Hot gas path component having near wall cooling features. United States.
Miranda, Carlos Miguel, Kottilingam, Srikanth Chandrudu, and Lacy, Benjamin Paul. 2017. "Hot gas path component having near wall cooling features". United States. doi:. https://www.osti.gov/servlets/purl/1410544.
@article{osti_1410544,
title = {Hot gas path component having near wall cooling features},
author = {Miranda, Carlos Miguel and Kottilingam, Srikanth Chandrudu and Lacy, Benjamin Paul},
abstractNote = {A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = 2017,
month =
}

Patent:

Save / Share:
  • A turbine airfoil is provided with at least one insert positioned in a cavity in an airfoil interior. The insert extends along a span-wise extent of the turbine airfoil and includes first and second opposite faces. A first near-wall cooling channel is defined between the first face and a pressure sidewall of an airfoil outer wall. A second near-wall cooling channel is defined between the second face and a suction sidewall of the airfoil outer wall. The insert is configured to occupy an inactive volume in the airfoil interior so as to displace a coolant flow in the cavity towardmore » the first and second near-wall cooling channels. A locating feature engages the insert with the outer wall for supporting the insert in position. The locating feature is configured to control flow of the coolant through the first or second near-wall cooling channel.« less
  • A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface ofmore » the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.« less
  • A combustor for a stationary combustor turbine is provided with a generally tubular sidewall formed from a telescopic arrangement of sidewall ring members. A corrugated spacer band supports the upstream end portion of each sidewall member on the downstream end portion of the next inwardly located sidewall member in the upstream direction. An annular coolant admission slot is thus provided between the sidewall members with the corrugated spacer band located therein. The downstream end portion of each sidewall member extends as an annular lip projecting downstream from the downstream end of the corrugated band to discourage mixing of the hotmore » internal gases with the coolant air flowing as a film through the slot and along the inner sidewall surface. Thermal load is transmitted from the inner sidewall member through the corrugated band to the upstream end portion of the outer sidewall member where a slotted wall structure enables outer wall deflection which in turn permits radial growth of the inner sidewall member and its extended lip substantially without disturbing the slot coolant flow.« less
  • A cooling channel (36, 36B, 63-66) cools inner surfaces (48, 50) of exterior walls (41, 43) of a component (20, 60). Interior side surfaces (52, 54) of the channel converge to a waist (W2), forming an hourglass shaped transverse profile (46). The inner surfaces (48, 50) may have fins (44) aligned with the coolant flow (22). The fins may have a transverse profile (56A, 56B) highest at mid-width of the inner surfaces (48, 50). Turbulators (92) may be provided on the side surfaces (52, 54) of the channel, and may urge the coolant flow toward the inner surfaces (48, 50).more » Each turbulator (92) may have a peak (97) that defines the waist of the cooling channel. Each turbulator may have a convex upstream side (93). These elements increase coolant flow in the corners (C) of the channel to more uniformly and efficiently cool the exterior walls (41, 43).« less
  • A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.