US-12618336-B2 - Turbomachine impingement cooling modules

US12618336B2US 12618336 B2US12618336 B2US 12618336B2US-12618336-B2

Abstract

An impingement module for localized cooling a hot gas path component of a turbomachine includes a plurality of impingement orifices. The impingement module is positioned with the plurality of impingement orifices oriented towards an outer surface of the hot gas path component. Thus, the impingement module is configured to receive a flow of pressurized air and direct the pressurized air through the impingement orifices to impinge on the outer surface of the component.

Inventors

Jonathan Dwight Berry

Assignees

GE VERNOVA INFRASTRUCTURE TECHNOLOGY LLC

Dates

Publication Date: 20260505
Application Date: 20240930

Claims (20)

1 . A turbomachine, comprising: a compressor extending from an inlet to a discharge, the discharge of the compressor providing a flow of high pressure air directly into a high pressure plenum defined within an outer casing of the turbomachine; a combustor at least partially surrounded by the outer casing; and a turbine downstream of the combustor, wherein the combustor comprises: a head end; a liner at least partially defining a hot gas path; a flow sleeve circumferentially surrounding at least a portion of the liner, wherein the flow sleeve is spaced from the liner to form a cooling flow annulus therebetween, the cooling flow annulus in fluid communication with the high pressure plenum whereby air from the high pressure plenum flows into the cooling flow annulus and from the cooling flow annulus to the head end; and an impingement module comprising a plurality of impingement orifices and a supply tube, the supply tube extending from an inlet to an outlet, the inlet of the supply tube flush with an outer surface of the flow sleeve whereby the inlet of the supply tube is positioned and oriented to receive a flow of air from the high pressure plenum, the supply tube extending from the inlet through the flow sleeve and radially inward from the flow sleeve to the outlet in the cooling flow annulus, wherein the outlet of the supply tube is coupled directly to a main body of the impingement module, whereby the flow of air flows directly into an internal plenum within the main body of the impingement module via the supply tube, with the plurality of impingement orifices oriented towards an outer surface of the liner whereby the impingement module is configured to direct the flow of air from the high pressure plenum through the impingement orifices to impinge on the outer surface of the liner.
2 . The turbomachine of claim 1 , wherein the impingement module comprises a plurality of impingement channels, wherein the plurality of impingement orifices is defined in the impingement channels.
3 . The turbomachine of claim 2 , wherein the impingement module further comprises one or more return channels defined between adjacent impingement channels of the plurality of impingement channels.
4 . The turbomachine of claim 3 , wherein the one or more return channels are positioned above the plurality of impingement orifices.
5 . The turbomachine of claim 1 , wherein the impingement module comprises a distribution channel upstream of the plurality of impingement orifices.
6 . The turbomachine of claim 1 , wherein each impingement orifice of the plurality of impingement orifices is spaced apart from the outer surface of the liner by a height, wherein each impingement orifice of the plurality of impingement orifices defines a diameter, and wherein the height at each impingement orifice is between one time and five times the diameter of the respective impingement orifice.
7 . The turbomachine of claim 1 , wherein the impingement module comprises a plurality of impingement channels, wherein the plurality of impingement orifices is equally distributed among the impingement channels.
8 . The turbomachine of claim 7 , wherein the impingement module comprises a distribution channel, the distribution channel upstream of the plurality of impingement channels, wherein the plurality of impingement channels is generally parallel to each other, and the distribution channel is oriented generally perpendicular to the plurality of impingement channels.
9 . The turbomachine of claim 8 , wherein the supply tube extends radially outward from the distribution channel.
10 . An impingement module for localized cooling a hot gas path component of a turbomachine, the impingement module comprising: a main body with an internal plenum defined within the main body; a supply tube extending from an inlet to an outlet, the inlet of the supply tube positioned and oriented to receive a flow of pressurized air, the outlet of the supply tube coupled directly to the main body of the impingement module, whereby the flow of pressurized air flows directly into the internal plenum within the main body of the impingement module via the supply tube; a plurality of impingement orifices, the impingement module positioned with the plurality of impingement orifices oriented towards an outer surface of the hot gas path component whereby the impingement module is configured to receive the flow of pressurized air into the internal plenum within the main body and direct the pressurized air from the internal plenum within the main body through the impingement orifices to impinge on the outer surface of the hot gas path component.
11 . The impingement module of claim 10 , further comprising a plurality of impingement channels, wherein the plurality of impingement orifices is defined in the impingement channels.
12 . The impingement module of claim 11 , further comprising one or more return channels defined between adjacent impingement channels of the plurality of impingement channels.
13 . The impingement module of claim 12 , wherein the one or more return channels are positioned above the plurality of impingement orifices.
14 . The impingement module of claim 10 , further comprising a distribution channel upstream of the plurality of impingement orifices.
15 . A flow sleeve for a combustor, the combustor comprising a liner at least partially defining a hot gas path wherein the flow sleeve is configured to mount to the combustor whereby the flow sleeve circumferentially surrounds at least a portion of the liner with the flow sleeve spaced from the liner to form a cooling flow annulus therebetween, the flow sleeve comprising: a supply tube extending from an inlet to an outlet, the inlet of the supply tube flush with an outer surface of the flow sleeve, the supply tube extending from the inlet through the flow sleeve and radially inward towards the liner from the flow sleeve to the outlet; and an impingement module coupled to the supply tube, the impingement module comprising: a main body with an internal plenum defined within the main body, and a plurality of impingement orifices, wherein the outlet of the supply tube is coupled directly to the main body of the impingement module, whereby a flow of air flows directly into the internal plenum within the main body of the impingement module via the supply tube, the impingement module positioned with the plurality of impingement orifices oriented towards an outer surface of the liner whereby the impingement module is configured to direct the flow of air from the internal plenum within the main body through the impingement orifices to impinge on the outer surface of the liner.
16 . The flow sleeve of claim 15 , wherein the impingement module comprises a plurality of impingement channels, wherein the plurality of impingement orifices is defined in the plurality of impingement channels.
17 . The flow sleeve of claim 15 , wherein each impingement orifice of the plurality of impingement orifices is spaced apart from the outer surface of the liner by a height, wherein each impingement orifice of the plurality of impingement orifices defines a diameter, and wherein the height at each impingement orifice is between one time and five times the diameter of the respective impingement orifice.
18 . The turbomachine of claim 1 , wherein the internal plenum is defined entirely within the main body of the impingement module, and wherein the main body of the impingement module is positioned entirely within the cooling flow annulus and spaced apart from each of the liner and the flow sleeve.
19 . The impingement module of claim 10 , wherein the internal plenum is defined entirely within the main body of the impingement module, and wherein the internal plenum is the only plenum of the impingement module.
20 . The flow sleeve of claim 15 , wherein the internal plenum is defined entirely within the main body of the impingement module, and wherein the main body of the impingement module is spaced apart from an inner surface of the flow sleeve.

Description

FIELD The present disclosure relates generally to hot gas path components, e.g., combustors, for turbomachines. More particularly, the present disclosure relates to systems for cooling such components. BACKGROUND Turbomachines are utilized in a variety of industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section progressively increases the pressure of a working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and a fuel (e.g., natural gas) mix within the combustion section and burn in a combustion chamber to generate high pressure and high temperature combustion gases. The combustion gases flow from the combustion section into the turbine section where they expand to produce work. For example, expansion of the combustion gases in the turbine section may rotate a rotor shaft connected, e.g., to a generator to produce electricity. The combustion gases then exit the gas turbine via the exhaust section. In many turbomachine combustors, combustion gases are routed towards an inlet of the turbine section of the gas turbine engine through a hot gas path that is at least partially defined by a combustion liner that extends downstream from a fuel nozzle and terminates at the inlet to the turbine section. Accordingly, high combustion gas temperatures within the turbine section generally correspond to greater thermal and kinetic energy transfer between the combustion gases and the turbine, thereby enhancing overall power output of the turbomachine. However, the high combustion gas temperatures may lead to erosion, creep, and/or low cycle fatigue to the various components of the combustor, thereby limiting overall durability of the combustor. Thus, it is necessary to cool the components of the turbomachine which lie along the hot gas path, such as the combustion liner. For example, cooling of the combustion liner is typically achieved by routing a cooling medium, such as the compressed working fluid from the compressor section, through a cooling flow annulus or flow passage defined between the liner and a flow sleeve and/or an impingement sleeve that surrounds the liner. The flow of cooling medium in the flow passage, e.g., between the liner and the sleeve, may become turbulent such that contact between the cooling medium and the hot gas path surface to be cooled, e.g., outer surface of the combustion liner, is inconsistent in direction and/or duration. Thus, such cross-flow or turbulent flow may result in reduced cooling of the hot gas path surface. Additionally, variations in the flow and/or concentration of high temperature combustion gases, as well as variations in the structure of the hot gas path components (e.g., such that portions of the hot gas path component are on the lee side of other components, such as on the lee side of axially-staged fuel injectors) may lead to development of localized heat concentrations, e.g., hot spots, where the temperature of the hot gas path component may be significantly higher than adjoining areas. Accordingly, an improved system for cooling a turbomachine combustor is desired in the art. In particular, a system which provides localized cooling, e.g., at one or more hot spots, and/or which provides impingement cooling with controlled and even flow to minimize or avoid cross-flow, would be useful. BRIEF DESCRIPTION Aspects and advantages of the systems in accordance with the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the technology. In accordance with one embodiment, a turbomachine is provided. The turbomachine includes a compressor, a combustor, and a turbine downstream of the combustor. The compressor extends from an inlet to a discharge. The discharge of the compressor provides a flow of high pressure air directly into a high pressure plenum defined within an outer casing of the turbomachine. The combustor includes a head end, a liner at least partially defining a hot gas path, a flow sleeve circumferentially surrounding at least a portion of the liner, and an impingement module. The flow sleeve is spaced from the liner to form a cooling flow annulus therebetween. The cooling flow annulus is in fluid communication with the high pressure plenum whereby air from the high pressure plenum flows into the cooling flow annulus and from the cooling flow annulus to the head end. The impingement module extends into the cooling flow annulus with the plurality of impingement orifices oriented towards an outer surface of the liner. Thus, the impingement module is configured to direct a flow of air from the high pressure plenum through the impingement orifices to impinge on the outer surface of the liner. In accordance with another embo