DE102015102560A1 - Exhaust chamber for radial diffuser - Google Patents

Abstract

An exhaust diffuser for a turbomachine includes a diffuser disposed on a turbine rotor and aligned with an axis of the turbine rotor. The diffuser is configured to deflect turbine exhaust gas substantially 90 degrees from a first flow direction along the first axis. An exhaust chamber is in fluid communication with and encloses an outlet end of a diffuser. The exhaust chamber is in fluid communication with a connection channel configured to provide exhaust gas to another turbomachine. The exhaust gas chamber expands on the volume between the diffuser and the connecting channel.

Description

Background of the invention

This invention relates generally to systems of heat recovery steam generators (HRSG) with gas turbine exhaust components, and more particularly to a turbine exhaust gas chamber configured to assist a uniform flow of exhaust gas into the heat recovery steam generator.

In gas and steam combined cycle power plant systems, heated exhaust gas from the gas turbines may be used by the heat recovery steam generator systems as a source of heat that may be transmitted to a source of water to produce superheated steam. The superheated steam can be used in the steam turbines as an energy source. The heated exhaust from a gas turbine may be transferred to the heat recovery steam generator system via, inter alia, an exhaust chamber and a diffuser which may help to convert the kinetic energy of the exhaust gas heated in the last stage of the gas turbine into potential energy in the form of increased static pressure. Once delivered to the heat recovery steam generator system, the heated exhaust gas may flow through a series of heat exchanger elements, such as superheaters, reheaters, evaporators, preheaters, and so on. The heat exchanger elements may be used to transfer heat from the heated exhaust gas to the water source to produce superheated steam. It is a design goal to support a uniform flow through the exhaust gas chamber without adversely affecting the diffuser performance, that is to allow diffusion flow with no perceptible total pressure drop.

Brief description of the invention

In one embodiment, an exhaust diffuser for a turbomachine is provided having a turbine rotor disposed in a diffuser axially aligned with the axis of the turbine rotor, the diffuser configured to substantially 90 degrees from a first flow direction along the turbine exhaust gas To deflect the axis; an exhaust chamber in fluid communication with an outlet end and enclosing that of the diffuser, the exhaust chamber being in fluid communication with a connection channel configured to supply the exhaust gas to another turbomachine; wherein the exhaust chamber widens in a direction toward the connection channel with respect to the volume.

In another embodiment, there is a turbomachine having a gas turbine section having a turbine rotor; a radial diffuser is aligned along a first axis of the turbine rotor; an exhaust chamber having an inlet that receives a portion of the radial diffuser, the exhaust chamber extending along a second axis that is substantially perpendicular to the first axis, wherein the exhaust chamber expands relative to the volume along the second axis.

In yet another embodiment, there is a gas and steam combined cycle power plant system comprising:
a gas turbine having a turbine rotor extending along a first axis; an exhaust steam generator; a steam turbine configured to receive steam from the exhaust steam generator; a radial diffuser disposed along the first axis; and an exhaust chamber having an inlet receiving a portion of the radial diffuser, the exhaust chamber extending along a second axis substantially perpendicular to the first axis, the exhaust chamber expanding and contracting with respect to volume along the second axis the exhaust steam generator is in communication.

 In any of the above-mentioned embodiments, it may be advantageous for the exhaust chamber to be partially contained within a pair of non-parallel sidewalls and a peripheral rim wall connecting the pair of non-parallel sidewalls.

 It may be advantageous for one wall of the pair of non-parallel sidewalls to be oriented substantially perpendicular to the axis.

 It may be advantageous for the other wall of the pair of non-parallel sidewalls to be oriented at an angle of 20 ° to 50 ° or 35 ° to 45 ° relative to the one wall of the non-parallel sidewalls.

 It may be advantageous that the peripheral edge wall has a radiused end portion connected to a pair of upper and lower wall portions that are straight and substantially parallel.

 It may be advantageous that the radiused end portion on one side of the axle and the pair of straight, substantially parallel upper and lower wall portions, respectively, traverse this axis and connect to the connection channel on an opposite side of the axle.

Brief description of the drawings

These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings, in which like reference characters represent like parts throughout the drawings, wherein:

1 Figure 3 is a schematic flow diagram of one embodiment of a gas and steam combined cycle power plant system including a gas turbine, a steam turbine, and a heat recovery steam generator;

2 a detailed, only partial side view of an embodiment of the gas turbine 1 is, the heat exchanger elements of the heat recovery steam generator off 1 integrated with components of an exhaust gas diffuser of the gas turbine;

3 a partially cutaway perspective view of an exhaust gas chamber in the manner, as in the gas turbine after 2 can be used;

4 a partially sectioned plan view of the 3 shown exhaust gas chamber is;

5 Figure 4 is a perspective view of an exhaust diffuser and a chamber in accordance with an exemplary, but not limited, embodiment of the invention;

6 another perspective view of the in 5 shown exhaust gas diffuser and the chamber is; and

7 is a plan view of the exhaust gas diffuser and the chamber, which in the 5 and 6 are shown.

Detailed description of the invention

 One or more concrete embodiments of the present invention will be described below. It is intended to provide a succinct description of these embodiments, and not all features of an actual implementation may be described in the description. It should be understood that in developing any actual implementation, as with any engineering or design project, a variety of implementation-dependent decisions must be made to achieve the developer's specific goals, such as compliance with systemic and business-related constraints vary from one implementation to another. In addition, it should be understood that such development work is complex and time consuming, but nonetheless a routine design, fabrication, and fabrication project for those skilled in the art who will benefit from this disclosure.

 When elements of the various embodiments of the present invention are introduced, the articles "one," "the," and "this," mean one or more these elements are present. The terms "comprising," "containing," and "having" are to be understood as inclusive, meaning that additional elements other than the specified elements may be present. Any examples of operating parameters are not exclusive of other parameters of the disclosed embodiments.

1 FIG. 4 is a schematic flowchart of one embodiment of a gas and steam combined cycle power plant system. FIG 10 with a gas turbine, a steam turbine and an exhaust steam generator. In particular, the system can 10 a gas turbine 12 to drive a first load 14 exhibit. The first load 14 For example, it may be an electrical generator for generating electrical power. The gas turbine 12 can a turbine 16 , a combustion chamber device 18 and a compressor 20 exhibit. The system 10 can also use a steam turbine 22 for driving a second load 24 exhibit. The second load 24 may also be an electrical generator for generating electrical power. It is understood, however, that both the first and the second load 14 . 24 may also be another type of load that is capable of passing through the gas turbine 12 and the steam turbine 22 to be driven. In addition, although the gas turbine 12 and the steam turbine 22 different loads 14 and 24 can drive, as shown in the illustrated embodiment, the gas turbine 12 and the steam turbine 22 also be used to drive in tandem operation a single load on a single shaft. In the illustrated embodiment, the steam turbine may have a low pressure section 26 (LP ST), a medium pressure section 28 (IP ST) and a high pressure section 30 (HP ST). However, the specific configuration of the steam turbine 22 as well as the gas turbine 12 , be application-dependent and have any combination of sections and / or stages.

The system 10 can also be a multi-stage heat recovery steam generator 32 exhibit. The simplified illustration of the heat recovery steam generator 32 and its components is not meant to be limiting. Rather, the illustrated heat recovery steam generator 32 to convey the general implementation of such systems. Heated exhaust 34 the gas turbine 12 can in the heat recovery steam generator 32 transported and used to heat steam, which is used to operate the steam turbine 22 is used. Exhaust from the low pressure section 26 the steam turbine 22 can be in a capacitor 36 be directed. The condensate of the condenser 36 in turn, in the low pressure section of the heat recovery steam generator 32 with the help of a condensate pump 38 be directed.

The condensate can then pass through a low pressure preheater 40 (LPECON), which is a device designed to heat feed water by means of gases, which can be used to heat the condensate. From the low pressure preheater 40 The condensate can either be in a low pressure evaporator 42 (LPIVAP) or to a medium pressure preheater 44 (IPECON). The vapor from the low pressure evaporator 42 can to the low pressure section 26 the steam turbine 22 to be led back. Accordingly, the condensate from the medium-pressure preheater 44 either in a medium pressure evaporator 46 (IPEVAP) or a high pressure evaporator 48 (HPECON). In addition, steam from the intermediate pressure evaporator 44 to a fuel gas heater (not shown) where the steam may be used to provide fuel gas for use in the fuel chamber assembly 18 the gas turbine 12 to heat. The vapor from the medium pressure evaporator 46 may go to the medium pressure section 28 the steam turbine 22 be transmitted.

Ultimately, condensate from the high pressure preheater 48 in a high pressure evaporator 50 (HPEVAP). Steam, the high pressure evaporator 50 Leaves, can be in a primary high pressure superheater 52 and an end high pressure superheater 54 be directed, where the steam is overheated and possibly to a high pressure section 30 the steam turbine 22 is transmitted. Exhaust from the high pressure section 30 the steam turbine 22 can turn into the medium pressure section 28 the steam turbine 22 be passed and exhaust gas from the medium-pressure section 28 the steam turbine 22 can in the low pressure section 26 the steam turbine 22 be directed.

An intermediate stage steam cooler 56 can be between the primary high pressure superheater 52 and the end high pressure superheater 54 be arranged. The intermediate stage steam cooler 56 can be a more robust control of the outlet temperature of the steam from the end high-pressure superheater 54 enable.

In addition, exhaust gas from the high pressure section 30 the steam turbine 22 in a primary reheater 58 and a secondary reheater 60 where it is reheated before it enters the intermediate pressure section 28 the steam turbine 22 is directed. The primary reheater 58 and the secondary reheater 60 can also use an intermediate stage steam cooler 62 to control the output steam temperatures of the reheaters.

In a gas and steam combined cycle power plant system 10 , can be hot exhaust gas from the gas turbine 12 Stream and through the heat recovery steam generator 32 flow and can be used to generate high pressure, high temperature steam. The steam coming from the heat recovery steam generator 32 is generated, then through the steam turbine 22 be led to energy production. In addition, the generated steam may also be provided to any other processes in which superheated steam may be used. The production cycle with the gas turbine 12 is often referred to as the "topping cycle" during the steam cycle generation cycle 22 often referred to as a "bottoming cycle". The combination of these two cycles, as in 1 illustrates the gas and steam combined cycle power plant system 10 achieve higher efficiency in both cycles. In particular, waste heat may be taken from the upstream cycle and used to generate steam in the downstream cycle.

Therefore, one aspect of the gas and steam combined cycle power plant system 10 the ability to heat from the heated exhaust 34 using the heat recovery steam generator 32 regain. As in 1 illustrates components of the gas turbine 12 and the steam generator 32 be separated into independent functional units. In other words, the gas turbine 12 the heated exhaust 34 generate and the heated exhaust 34 to the heat recovery steam generator 32 which may be mainly responsible for the heat from the heated exhaust gas 34 by recovering superheated steam. The superheated steam can turn in the steam turbine 22 be used as an energy source. The heated exhaust 34 can go to the heat recovery steam generator 32 be routed through a conduit arrangement based on the concrete design of the gas and steam combined cycle power plant system 10 can vary.

A more detailed presentation like the gas turbine 12 functioning can contribute to the illustration, like the heated exhaust 34 from the gas turbine 12 to the heat recovery steam generator 32 can be brought. Corresponding is 2 a detailed side view of an embodiment of the gas turbine 12 to 1 with heat exchanger elements of the heat recovery steam generator 32 to 1 , With integrated components of an exhaust gas diffuser of the gas turbine 12 , As related to 1 described, the gas turbine 12 the turbine 16 , the combustor 18 and the compressor 20 exhibit. Air can pass through an air inlet 64 enter and through the compressor 20 be compressed. Subsequently, the compressed air from the compressor 20 into the combustion chamber 18 where the compressed air is mixed with fuel gas. The fuel gas may enter the combustor 18 through a plurality of fuel nozzles 66 be initiated. The mixture of compressed air and fuel gas becomes substantially within the combustion chamber of the combustor 18 burned to produce a high temperature, high pressure exhaust that can be used to generate torque in the turbine 16 to create. A rotor of the turbine 16 can with a rotor of the compressor 20 be coupled, so that the rotation of the turbine rotor is also a rotation of the compressor 20 can cause. This is how the turbine drives 16 the compressor 20 as well as the load 14 (in 2 not shown). Exhaust gas from the turbine section of the gas turbine 12 can in an exhaust diffuser 68 be directed. According to the embodiment 2 , the exhaust diffuser can 68 a radial exhaust gas diffuser, wherein the exhaust gas through Ausgangsleitflügel 70 can be deflected to the exhaust diffuser 68 by a 90 degree outward change (ie, radial) through an exhaust chamber (not shown) and a connection entrance to the heat recovery steam generator 32 leave.

Another aspect of certain components of the exhaust diffuser 68 in addition to steering the heated exhaust gas 34 to the heat recovery steam generator 32 may be to ensure that certain aerodynamic properties of the heated exhaust gas 34 be achieved. For example, an exhaust frame strut 72 as they are in 2 is illustrated, curved with an enveloping arranged thereon be air duct. The exhaust frame strut 72 can also be rotated, such that a twist of the heated exhaust gas 34 minimizes and the flow of heated exhaust gas 34 generally more axial in nature, to flow through the exit vanes 70 , In addition, the exit fins 70 also be designed such that when the heated exhaust gas 34 is deflected to the exhaust chamber by a 90-degree angle, the Auslassleitflügel 70 minimize the aerodynamic losses that occur when deflecting the flow by 90 ° in the radial direction. Therefore, a suitable aerodynamic design of the exhaust frame strut 72 , the outlet vane 70 and other components of the exhaust diffuser 68 within the flow path of the heated exhaust gas 34 to be considered in the design.

3 is a sectional perspective view of an embodiment of a diffuser, which is equal to the diffuser 68 out 2 It can be seen that the diffuser, for the sake of simplicity, is not on the same scale as in FIG 2 is shown. The diffuser 68 is with a chamber 74 connected, which together with the guide vanes 46 the exhaust gas is substantially ninety (90) degrees into a connecting channel 76 deflected, which is connected to the heat recovery steam generator inlet (not shown). The radial guide vanes 46 may be circular (for example frustoconical annular or conical in shape) and concentric about the x-axis 31 be arranged. The chamber 74 directs the exhaust gases along the z-axis 35 then gradually into the widening transitional section 76 , which is connected to the inlet of the heat recovery steam generator.

The chamber 74 has in the known configuration that in the 3 and 4 is shown, a substantially square or rectangular shape, but with a tapered Endwandabschnitt 78 that extends from the upper wall 80 to a side wall 82 extends. The walls 80 and 82 are aligned substantially perpendicular to each other while the upstream and downstream sides 84 . 86 are parallel what is best in 4 can be seen. The bottom wall 88 is parallel to the top wall 80 but may have a bevelled component 90 between the bottom wall 88 and the side wall 82 exhibit.

5 to 7 illustrate a modified chamber 100 in accordance with an exemplary, but non-limiting embodiment of the invention. The radial diffuser 101 is received in the chamber inlet, concentric with the turbine rotor axis 114 ( 7 ). In this example is the chamber 100 designed with a radius curved end by a curved end wall 102 is formed with the upper and the lower wall 104 . 106 connected is. The curved end wall 102 and the top and bottom walls 104 . 106 together form a respective peripheral wall, an upstream side and a downstream side wall 108 . 110 extending from the curved end wall 102 to the expanding connecting section 112 extend. The curved end wall 102 refers to the central axis 114 of the diffuser 101 (again, not drawn to scale), and the top and bottom walls 104 . 106 extend tangentially, parallel to each other, away from opposite ends of the curved end wall. It should be noted that the straight upper and lower wall 104 . 106 the axis 114 traverse the diffuser / turbine rotor.

It will be understood that the internal conductive components of the diffuser are different from those in FIG 3 can be the same arrangement shown.

It is clear that the upstream and downstream sidewalls 108 and 110 are not parallel. How best in 7 can be seen, is the downstream side wall 110 perpendicular to the central axis 114 but the upstream side wall 108 extends at an angle of between 20 and 50 degrees (and preferably between 35 and 45 degrees) with respect to the downstream side wall 110 , This extension of the flow path from the chamber 100 to the connection section 112 assists redistribution to even out the gas flow to the heat recovery steam generator inlet without affecting the diffuser performance. In fact, the uniform flow not only positively affects the performance of the heat recovery steam generator but also simplifies the design of the heat recovery steam generator muffler located in the waste heat recovery steam generator inlet. The chamber design described herein also permits relatively flat inlet profiles over operating conditions and over a range of the final stage turbine blade exit profile.

8th illustrates heat recovery steam generator inlet profiles in the chamber exit plane 116 and at the downstream edge 118 of the connection section 112 , The y-axis "% distance" refers to the height of the chamber from the bottom to the top. It can be seen that the "overall velocity" of the air flow through the chamber is relatively uniform across the height of the chamber.

While the invention has been described in conjunction with what is presently believed to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiment but, on the contrary, is intended to encompass various modifications and equivalent arrangements within the scope of the present invention to include the appended claims.

An exhaust diffuser for a turbomachine includes a diffuser disposed on a turbine rotor and aligned with an axis of that turbine rotor. The diffuser is configured to divert the turbine exhaust gas substantially 90 degrees from a first flow direction along the rotor axis. An exhaust chamber is in fluid communication with and surrounds an outlet end of the diffuser. The exhaust chamber is in fluid communication with a connection channel configured to provide the exhaust gas to another turbomachine. The exhaust chamber widens in relation to the volume between the diffuser and the connecting channel.

LIST OF REFERENCE NUMBERS

 10

system

12

gas turbine

14

first load

16

turbine

18

combustor

20

compressor

22

steam turbine

24

second load

26

Low pressure section (LP ST)

28

Intermediate pressure section (IP ST)

30

High pressure section (HP ST)

32

multi-stage heat recovery steam generator (HRSG)

34

heated exhaust

36

capacitor

38

condenser pump

40

Low pressure preheater (LPECON)

42

Low pressure evaporator (LPEVAP)

44

Intermediate pressure preheater (IPECON)

46

Intermediate pressure evaporator (IPEVAP)

48

High pressure preheater (HPECON)

50

High pressure evaporator (HPEVAP)

 52

Primary high-pressure superheater

54

End high-pressure superheater

 56

Intermediates Desuperheaters

58

Primary reheater

60

Secondary reheaters

62

Intermediates Desuperheaters

64

air intake

66

fuel nozzles

68

exhaust diffuser

70

Ausgangsleitflügel

 72

Exhaust frame strut

74

chamber

 76

connecting channel

78

bevelled end wall section

80

upper wall

82

Side wall

84

upstream side

86

downstream side

88

bottom wall

90

bevelled component

100

modified chamber

101

radial diffuser

102

curved end wall

 104

upper wall

106

bottom wall

108

upstream side wall

110

downstream side wall

 112

connecting portion

114

Turbine rotor axis (first axis)

116

Chamber exit plane (second axis)

118

Downstream edge

Claims (10)

Exhaust diffuser for a turbomachine comprising: a diffuser disposed in a turbine rotor and aligned with an axis of that turbine rotor, the diffuser configured to deflect turbine exhaust gas substantially 90 degrees from a first flow direction along the axis; an exhaust chamber disposed in fluid communication with and surrounding an outlet end of the diffuser, the exhaust chamber in fluid communication with a connection channel configured to provide exhaust gas to another turbomachine; wherein the exhaust chamber widens in volume in a direction toward the connection channel. The exhaust diffuser of claim 1, wherein the exhaust chamber is partially contained in a pair of non-parallel side walls and a peripheral edge wall connecting the pair of non-parallel side walls. The exhaust diffuser of claim 2, wherein one side wall of the pair of non-parallel sidewalls is disposed substantially perpendicular to that axis and / or the other sidewall of that pair of non-parallel sidewalls faces at an angle of 20-50 ° or 35-45 ° which extends one of these non-parallel side walls. The exhaust diffuser of claim 2, wherein the peripheral rim wall has a curved end portion connected to a pair of upper and lower wall portions that are straight and substantially parallel. The exhaust diffuser of claim 4, wherein the curved end portion is disposed on a side of this axis and the pair of upper and lower wall portions that are straight and substantially parallel traverse that axis and are connected to the connection channel on an opposite side of that axis. Turbomachine comprising: a gas turbine section having a turbine rotor; a radial diffuser disposed along a first axis of the turbine rotor; an exhaust chamber having an inlet receiving a portion of the radial diffuser, the exhaust chamber extending along a second axis substantially perpendicular to that first axis, the exhaust chamber expanding in volume along the second axis. Turbomachine according to claim 6, wherein the exhaust chamber is partially contained in a pair of non-parallel side walls and a peripheral edge wall connecting the pair of non-parallel side walls. The turbomachine of claim 7, wherein one wall of the pair of non-parallel sidewalls is oriented substantially perpendicular to that axis. A turbomachine according to claim 8, wherein the other wall of said pair of non-parallel side walls extends at an angle of 20-50 ° or 35-45 ° with respect to the one wall of said pair of non-parallel side walls. Gas and steam combined cycle power plant system comprising: a gas turbine comprising a turbine rotor extending along a first axis; a heat recovery steam generator; a steam turbine configured to receive steam from the heat recovery steam generator; a radial diffuser disposed along the first axis; and an exhaust chamber having an inlet receiving a portion of the radial diffuser, the exhaust chamber extending along a second axis substantially perpendicular to the first axis, the exhaust chamber expanding and contiguous with the volume along said second axis communicates with the heat recovery steam generator.

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