JPH1054258A - Compressor, combustion turbine and combustion turbine cooling method - Google Patents

Abstract

PROBLEM TO BE SOLVED: To make NOx in exhaust gas extremely low by diverging part of discharge air of a compressor at the inner diameter face of a compressor outlet, compressing this air in a compression stage positioned on the lower side of an internal wall of a main compressor outlet diffuser, and installing the main compressor outlet diffuser downstream adjacently to an auxiliary compressor. SOLUTION: A combustion turbine 10 has a plural rows of compressor blades, and a set 20 of a fixed blade and an outlet guide blade is provided directly downstream of the compressor blade 12 in the last row. Air flow passing through this set 20 flows through a main compressor outlet diffuser 30. Main air flow in this diffuser 30 is divided in a main part 32 and auxiliary air flow 34 by an internal wall (partition) 36, and the auxiliary air flow 34 is led to an auxiliary air compressor 50 arranged adjacently to the lower side of the internal wall 36 of the main compressor outlet diffuser 30. The auxiliary air compressor 50 is driven by a center main shaft 11 of the combustion turbine 10 so as to compress the auxiliary air flow 34 and to lead it again into a member to be cooled. Performance of the turbine is thereby improved, and extra-low NOx is emitted.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbomachine,
In particular, it relates to a structure of a compressor for a cooling device for a combustion turbine.

[0002]

BACKGROUND OF THE INVENTION It is known to extract air from a compressor, cool the air, and use the air to cool the turbine section of a combustion turbine. Some examples of such devices are disclosed in U.S. Pat.
No. 55,505 (Cloyd et al) and is incorporated herein by reference in its entirety.

[0003] Increasing the performance of a combustion turbine can be achieved using a closed loop air cooling system. in addition,
Ultra low NOx emission combustion combustion turbines require that almost all of the compressor air be premixed with fuel. In both of these devices, it is necessary to extract a portion of the compressor discharge air, cool it, and compress it with an external compressor. The compressed air is then reintroduced into the combustion turbine at the point used for cooling. However, adding an external compressor results in increased equipment complexity and manufacturing costs, and also creates the possibility of shutting down due to a failure of the auxiliary compressor or one of its controls.

The provision of an auxiliary centrifugal compressor at the inlet of the turbine blade and adjacent to the outlet of the combustion chamber is disclosed in US Pat. No. 3,936,215 (Hoff). This patent shows that the compressor outlet air loses sufficient pressure so that the combustion chamber cannot be effectively introduced into the turbine section where hot gas exits. It is here that the temperature is highest and cooling is needed,
Therefore, a small centrifugal compressor is interposed between the outlet of the combustion chamber and the inlet of the turbine section. A centrifugal compressor is supplied with air from the compressor, which is at a lower pressure than that which effectively cools due to its pressure loss.

[0005]

Thus, although it is known to provide an external centrifugal compressor to increase the pressure of the compressor discharge air, such devices are subject to the aforementioned complexity problems. I have The prior art centrifugal compressor inside the turbine is an ultra-low NOx emission combustion that is required for a closed loop air cooling system or where almost all of the compressor air is required to be premixed with fuel It does not provide the same flow specifications and heat exchange performance required for a conventional combustion turbine. Thus, for a method and apparatus in which an additional pressure is generated in the cooling air exiting the compressor,
There is a need to remain felt and unresolved for a long time.

[0006]

SUMMARY OF THE INVENTION However, the hot side component is cooled, either directly or by extraction from the combustion tube, and is cooled, and then pressurized pressurized air is reintroduced to the component to be cooled. It has now been found that auxiliary compressors which supply the required quantity overcome the deficiencies of the prior art. In a preferred embodiment, a portion of the compressor discharge air is diverted at the inner diameter of the compressor outlet and is provided by one or more low and high axial compression stages located below the inner wall of the main compressor outlet diffuser. Although compressed, the main compressor outlet diffuser is located downstream adjacent to the auxiliary compressor. The compressed air is then conveyed through passages to cool the combustor and turbine components, or removed from the tube via conduit. Those skilled in the art will be familiar with the use of such conduits and their use to cool combustion turbines.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT Referring first to FIG. 1, there is shown the general arrangement and operation of the components of a preferred embodiment of the present invention. Those skilled in the art will be familiar with the construction and operation of the equipment used in a combustion turbine. Various devices are not shown to more clearly illustrate the present invention, but some of the components of the combustion turbine are schematically illustrated in partial cross-section.

As shown in FIG. 1, a typical device includes a combustion turbine and a compressor 10, which has multiple rows of compressor blades. FIG. 1 shows the last row of compressor blades 12.
Is shown in FIG. Immediately downstream of the last row of compressor blades 12 is a last row of fixed blade and outlet guide blade sets 20. After passing through the fixed vane and guide vane set 20, the air flow passes through the main compressor outlet diffuser 30. However,
According to the present invention, the main airflow is divided by an inner wall or partition 36 into a main portion 32 and a sub-airflow 34. As indicated by the arrow in FIG.
Guided through. The auxiliary air compressor 50 is connected to and driven by the central main shaft 11 of the combustion turbine 10, and is separated from the last row of compressor blades 12 by the circular spacer 21. The secondary air compressor 50 is made up of one or more secondary compressor blades 52, most preferably having a small height relative to the compressor blades 12, and having a main compressor outlet diffuser 30. The lower side of the inner wall 36 (in the figure)
It is arranged adjacent to. The secondary air stream 34 is compressed as it enters the cascade and then exits through the secondary outlet diffuser. The auxiliary air compressor 50 cools the high temperature member by extracting this air directly or from the combustion cylinder,
This is cooled and supplied with pressurized air used to be reintroduced into the component to be cooled.

[0009] Compressed air is then carried directly through the passages to cool the combustor and other combustion turbine components, or to be removed from the tube via a conduit.
Those skilled in the art will be familiar with the use of such conduits and cooling of combustion turbines. The efficiency of the built-in sub-compressor obtained according to the invention is comparable to that of an external compressor of similar use.

[0010] In addition to the foregoing, it will be appreciated that the present invention also provides an improved method of cooling a combustion turbine. As described above, in conventional devices, the air exiting the compressor section is extracted from the compressor shell or combustion chamber and is disclosed in US Pat.
Cool as shown in US Pat. No. 5,505. However, in accordance with the present invention, the improvement in efficiency and reliability is achieved by first splitting the compressor outlet stream into a main portion and a smaller portion, and then directing the smaller portion of the compressor outlet flow to a sub-compressor. can get. According to a preferred embodiment of the present invention,
The compressor outlet stream is split by providing a partition across the main compressor outlet diffuser.

[0011] The sub-compressor of the present invention is most preferably arranged in a built-in manner, and a small portion of the main compressor outlet stream is preferably passed through one or more sub-axial compressor blades. By flowing a small portion, it is compressed into the sub-compressor outlet stream. In a preferred embodiment, the compressor is driven by a central main shaft 11 and the counter-axial compressor blades are connected to the main main shaft 11 and rotated. The sub-compressor outlet stream is passed directly to one or more combustors and other components through passages, or is transferred to one or more conduits for transfer to a heat exchanger. In both cases, the sub-compressor outlet stream is then cooled and reintroduced into the turbine.

[0012] Finally, the function of the axial-flow built-in sub-compressor described above is achieved by the centrifugal-flow compressor and the mixed-flow compressor. According to these embodiments of the present invention, the sub-compressor is most preferably located adjacent and below the main compressor outlet diffuser. Although some embodiments of the invention have been described and described in detail herein, it is understood that these descriptions are intended to illustrate the features of the invention.
It should not be understood as limiting. Upon review of the above description, various modifications, adaptations and improvements to the disclosed methods and apparatus will readily occur to those skilled in the art. Such modifications, adaptations and improvements do not depart from the spirit of the invention and, for this reason, reference should be made to the appended claims in order to understand the full scope of the invention.

[Brief description of the drawings]

FIG. 1 is a partial schematic diagram illustrating a portion of a combustion turbine and related components incorporating the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 10 Combustion turbine, 11 Central main shaft, 12 Compressor blades, 20 Combination of fixed vane and outlet guide vane, 21 Circular spacer, 30 Main compressor outlet diffuser, 32 Main part, 34 Secondary air flow, 36 Partition, 50 Secondary air compression , 52 sub-compressor blades.

 ──────────────────────────────────────────────────続 き Continued on front page (72) Inventor David John Hoover United States, Ohio, North Canton, NE, No. 4, Beachwood Avenue 1783 (72) Inventor Nathan Richard Pfeiffer United States Glen Koub Circle, 10847, Number 106, Orlando, Florida

Claims (3)

[Claims] 1. A compressor having a plurality of rotary compressor blades and a set of fixed and outlet guide vanes, wherein the air is compressed into a main compressor outlet diffuser, the turbine further comprising: An integrated auxiliary air compressor is disposed adjacent the main compressor outlet diffuser and adjacent the last row of stationary vanes and outlet guide vanes for receiving a secondary air flow that forms part of the air flow exiting the compressor. And a compressor, wherein the auxiliary air compressor supplies air used to cool one or more components of the combustion turbine device at an increased pressure. 2. A sub-axial compressor directly adjacent to the last row of fixed vanes and outlet guide vanes, and a partition for dividing the main compressor outlet diffuser into a main portion and a sub-portion;
A combustion turbine wherein the partition defines an inlet communicating with the counter-axial compressor. 3. splitting the main compressor outlet stream into a major portion and a smaller portion; feeding the small portion of the main compressor outlet stream directly into a sub-compressor; Compressing the small portion of the stream into an outlet stream of the sub-compressor; cooling the outlet stream of the sub-compressor; and reintroducing the outlet stream of the sub-compressor into a turbine. How to cool a combustion turbine.