US20090074589A1

US20090074589A1 - Cooling Circuit for Enhancing Turbine Performance

Info

Publication number: US20090074589A1
Application number: US11/856,945
Authority: US
Inventors: Biao Fang; Christopher Edward Wolfe; Omprakash Samudrala; Matthew Scott Kight; Jeffrey John Butkiewicz; Tara McGovern
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2007-09-18
Filing date: 2007-09-18
Publication date: 2009-03-19
Also published as: JP2009074549A; DE102008044495A1; CH697912A2; CH697912B1; CN101392687A

Abstract

In a gas turbine having a compressor discharge casing, a cooling circuit diverts compressor discharge air toward a high pressure packing (HPP) circuit. The cooling circuit includes an inlet pipe that receives compressor discharge air. One or several cooled cooling air pipes are in fluid communication with the inlet pipe via a pipe manifold, which distributes the discharge air across the cooled cooling air pipes. A seal is disposed upstream of an entrance to the HPP circuit to limit flow into the HPP circuit, and a second seal is disposed downstream of the HPP circuit at turbine wheelspace to limit ingestion and thus the purge flow air required. The circuit serves to reduce required purge flow in the HPP circuit so that an amount of compressor discharge air can be put back to the main flow path, thereby improving turbine performance.

Description

BACKGROUND OF THE INVENTION

The invention relates to a structure and method for enhancing turbine performance and, more particularly, to a cooling circuit that diverts compressor discharge air to supplement the total required purge flow and cool critical turbine components.
The compressor discharge air leaking past the high pressure packing (HPP) of a gas turbine is typically returned to the primary gas path via the first forward wheelspace, between the first stage nozzles and first stage buckets. This secondary flow path is referred to as the HPP circuit. This air is used for two purposes: (1) it is used as purge flow in the first wheelspace to prevent hot gas ingestion; and (2) it cools critical components in the HPP circuit. Some of the critical components in the HPP circuit include the compressor tie bolts, marriage joint, nozzle support ring and first stage wheel.
In some designs, the flow level in the HPP circuit is higher than the wheelspace purge requirement because of component temperature requirements. Therefore, an ideal solution should reduce the total circuit flow to a level that satisfies the wheelspace purge requirements while keeping all critical components in the circuit under desired temperature requirements. Furthermore, a preferred solution may also be able to handle robustly varying ambient and turbine operation conditions. Finally, the solution should be able to retrofit in the existing hardware.
In a previous General Electric turbine design (the 9H turbine), an HPP circuit utilized a cooled cooling air bypass system. The circuit used a heat exchanger to cool the extracted compressor discharge air and bring the cooled cooling air to the front of the HPP circuit to not only cool the last stages of the compressor components but also prevent a later stage flow from coming into the HPP circuit. This system uses conventional sealing that the HPP and makes no attempt to regulate the purge flow required beyond conventional angel wing seals. The cooled cooling air is not adjustable.
Brush seals have been implemented in other turbine designs to reduce the purge flow. No cooled cooling air is needed there, however, because of lower compressor discharge temperatures and consequently lower temperatures in the HPP circuit resulting in adequate wheelspace temperature margins.

BRIEF DESCRIPTION OF THE INVENTION

In an exemplary embodiment, a cooling circuit in a gas turbine serves to augment flow in a high pressure packing (HPP) circuit of the turbine. The cooling circuit includes an inlet pipe that receives compressor discharge air, and at least one cooled cooling air pipe in fluid communication with the inlet pipe via a pipe manifold. The pipe manifold distributes the discharge air across the at least one cooled cooling air pipe. An upstream seal is disposed upstream of an entrance to the HPP circuit, and a downstream seal is disposed downstream of the HPP circuit.
In another exemplary embodiment, a method of improving turbine performance using a cooling circuit by augmenting flow in a high pressure packing (HPP) circuit of the turbine includes the steps of receiving compressor discharge air in an inlet pipe; distributing the discharge air across a plurality of cooled cooling air pipes; and disposing an upstream seal upstream of an entrance to the HPP circuit to regulate air entering the HPP circuit and disposing a downstream seal downstream of the HPP circuit to regulate a need for wheelspace purge air.
In still another exemplary embodiment, the cooling circuit includes an inlet pipe that receives compressor discharge air; at least one cooled cooling air pipe in fluid communication with the inlet pipe via a pipe manifold, the pipe manifold distributing the discharge air across the at least one cooled cooling air pipe; a cooling source in direct contact with one of the at least one cooled cooling air pipe and the diverted air; a valve disposed between the inlet pipe and the at least one cooled cooling air pipe, the valve adjusting mass flow and a temperature of the diverted air based on a temperature of the HPP circuit; an upstream seal disposed upstream of an entrance to the HPP circuit; and a downstream seal disposed downstream of the HPP circuit.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows the cooling circuit of an exemplary embodiment; and

FIG. 2 shows the cooling circuit of an alternative exemplary embodiment.

DETAILED DESCRIPTION OF THE INVENTION

With reference to FIG. 1, the system utilizes a seal 12 such as a brush seal, adjustable seal, or the like to prevent excessive flow from the compressor discharge air and secondary (bypass) cooled cooling air system to supplement the total required purge flow and cool critical components. An adjustable seal can be one that is retracted during engine transients to minimize wear or damage to the seal, or one that allows for adjustment in service to accommodate seal performance degradation.
The seal 12 is placed upstream or adjacent the HPP circuit entrance before all critical components and the existing honeycomb seal. As noted, the seal can be a conventional brush seal, an adjustable seal with an actuating system, or the like.
An inlet tube or pipe 14 is positioned to receive compressor discharge air. Preferably, the circuit includes two inlet tubes or pipes 14 of about 3″ diameter.
Diverted air in the inlet pipe 14 is flowed to a plurality of cooled cooling air pipes 16 via a pipe manifold 18. The pipe manifold 18 distributes the discharge air from the inlet pipes 14 across the cooled cooling air pipes 16. The cooled cooling air pipes 16 direct the compressor discharge air to the HPP circuit.
In a preferred arrangement, the cooling circuit includes 12 cooled cooling air pipes that penetrate at the compressor discharge case vertical flange and run along the compressor discharge case strut at trailing edges. The cooled cooling air pipes are preferably ¾″ or 1″ in diameter. The positioning via the compressor discharge case struts serves to minimize the aerodynamic impact on the main gas flow. A computational fluid dynamics analysis has been conducted to ensure that the added tubing system has a negligible impact on the main gas flow. The tubes 16 further penetrate the compressor discharge casing inner barrel flange via suitable apertures.
The circuit preferably additionally includes a cooling source in communication with either or both of the inlet pipe 14 and the cooled cooling air pipes 16. In one arrangement, the cooling source comprises ambient air that serves to cool the air flow as it travels through the cooled cooling air pipes 16. Alternatively, the cooling source may comprise a heat exchanger 20 such as a tube-shell type heat exchanger or the like.
Still another alternative for the cooling source is an atomizer 22 that sprays water droplets in contact with either the diverted air or the cooled cooling air pipes 16. The atomizer 22 preferably generates micro-level water droplets that are sprayed directly to cool the extracted air. The amount of water required to cool the flow by 150° F. will elevate the main gas path flow moisture level by only 2%. Locally in the HPP circuit, the specific humidity will typically be 4-5 times compared to the condition at the inlet. This higher humidity in general is harmless to the circuit components.
FIG. 2 illustrates an alternative to the heat exchanger 20 or atomizer 22 shown in FIG. 1. FIG. 2 illustrates an ejector 24 that mixes air from the 13^thstage of the compressor, or other suitable compressor extraction port, with the compressor discharge air. The 13^thstage air is directed to the ejector via suitable tubing 26 or the like. The combined 13^thstage and compressor discharge air at the ejector exit will have a desired temperature and lower than the compressor discharge air pressure. Because relatively cheaper air from stage 13, cheaper in that less work has been done on the air to compress and heat it, is used, additional turbine performance can be gained.
The exit temperature and mass flow can be tuned by a valve 28 disposed between the inlet pipe 14 and the cooled cooling air pipes 16. An additional valve may be provided to control water mass when using the atomizer 22. The two valves can be operated either manually or automatically by control signals. Preferably, the valves can be automatically adjusted for desired mass flow and temperature of cooled cooling air based on a temperature measurement at the HPP circuit. Such valves can be used to regulate the CCA circuit regardless of the cooling mechanism used. These valves should be controlled based on temperature measurements made in the HPP circuit; these are typically made at several locations in the wheelspace, but can also be made at any critical location in the HPP circuit. Temperature measurements can be used to both determine that the cooling air is adequately cool, and to identify the hot gas ingestion into the wheelspace.
The cooled cooling air pipes 16 deliver the cooling air at various locations relative to the HPP circuit. As shown in FIGS. 1 and 2, openings 30 are preferably provided in the inner barrel in order to supply cooled cooling air to the tie bolt and marriage flange of the turbine. The remainder of the CCA is fed directly into the first forward wheelspace.
The system and method described endeavor to save the amount of compressor discharge air required in the HPP circuit and redirect it back to the main flow path to enhance turbine performance. This can be achieved robustly by introducing a secondary flow system to bring cooled cooling air in the circuit. The amount of the total flow required in the circuit is dictated by the wheelspace purge requirement. The difference between the wheelspace purge requirement and current flow is significant enough to justify the implementation of the secondary cooled cooling air circuit. A seal limits the air entering the HPP circuit to the minimum possible so that as much of the required purge air as possible is supplied by the cooled cooling air circuit. Improved sealing at the wheelspace via abradable angel wing seals reduces the amount of purge air required. The mixed compressor discharge air and cooled cooling air should be sufficient to prevent the wheelspace hot gas ingestion while keeping the critical components in the circuit under temperature limits.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not to be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

1. A cooling circuit in a gas turbine for augmenting flow in a high pressure packing (HPP) circuit of the turbine, the cooling circuit comprising:

an inlet pipe that receives compressor discharge air;

at least one cooled cooling air pipe in fluid communication with the inlet pipe via a pipe manifold, the pipe manifold distributing the discharge air across the at least one cooled cooling air pipe;

an upstream seal disposed upstream of an entrance to the HPP circuit; and

a downstream seal disposed downstream of the HPP circuit.

2. A cooling circuit according to claim 1, further comprising a cooling source in communication with the at least one cooled cooling air pipe.

3. A cooling circuit according to claim 2, wherein the cooling source comprises ambient air.

4. A cooling circuit according to claim 2, wherein the cooling source comprises a heat exchanger.

5. A cooling circuit according to claim 2, wherein the cooling source comprises an atomizer that sprays water droplets in contact with one of the diverted air and the at least one cooled cooling air pipe.

6. A cooling circuit according to claim 2, wherein the cooling source comprises an ejector that mixes air from at least two compressor stages including the compressor discharge.

7. A cooling circuit according to claim 1, wherein the cooled cooling air pipes penetrate a vertical flange of the compressor discharge casing and extend along a compressor discharge casing strut at trailing edges.

8. A cooling circuit according to claim 1, further comprising a valve disposed between the inlet pipe and the cooled cooling air pipes, the valve adjusting mass flow and a temperature of the diverted air based on a temperature of the HPP circuit.

9. A cooling circuit according to claim 1, further comprising openings in an inner barrel to permit cooled cooling air from the cooled cooling air pipes to reach at least one of a tie bolt and a marriage flange in the turbine.

10. A cooling circuit according to claim 1, wherein the downstream seal comprises an abradable angel wing seal.

11. A method of improving turbine performance using a cooling circuit by augmenting flow in a high pressure packing (HPP) circuit of the turbine, the method comprising:

receiving compressor discharge air in an inlet pipe;

distributing the discharge air across a plurality of cooled cooling air pipes; and

disposing an upstream seal upstream of an entrance to the HPP circuit to regulate air entering the HPP circuit and disposing a downstream seal downstream of the HPP circuit to regulate a need for wheelspace purge air.

12. A method according to claim 11, further comprising actively cooling the cooled cooling air pipes.

13. A method according to claim 12, wherein the actively cooling step is practiced using ambient air.

14. A method according to claim 12, wherein the actively cooling step is practiced using a heat exchanger.

15. A method according to claim 12, wherein the actively cooling step is practiced using an atomizer that sprays water droplets in contact with one of the diverted air and the cooled cooling air pipes.

16. A method according to claim 12, wherein the actively cooling step is practiced using an ejector that mixes air from at least two compressor stages.

17. A method according to claim 11, wherein the discharge air is regulated by a valve.

18. A cooling circuit in a gas turbine for augmenting flow in a high pressure packing (HPP) circuit of the turbine, the cooling circuit comprising:

an inlet pipe that receives compressor discharge air;

a cooling source in direct contact with one of the at least one cooled cooling air pipe and the diverted air;

a valve disposed between the inlet pipe and the at least one cooled cooling air pipe, the valve adjusting mass flow and a temperature of the diverted air based on a temperature of the HPP circuit;

an upstream seal disposed upstream of an entrance to the HPP circuit; and

a downstream seal disposed downstream of the HPP circuit.