DE102017112426A1 - Gas turbine machine with a countercurrent cooling system and method - Google Patents

Abstract

A gas turbine engine (2) includes a housing assembly (50) surrounding a portion of the gas turbine engine (2). The housing assembly (50) includes an inner housing portion (64) defining a housing volume V _C and a countercurrent cooling system (100) disposed within the inner housing portion (64). The counterflow cooling system (100) includes a plurality of channels (111, 196, 204, 207, 220) which together define a channel volume V _Ch . The plurality of channels (111, 196, 204, 207, 220) are configured and arranged to direct cooling fluid through the housing assembly (50) in a first axial direction and to return cooling fluid through the housing assembly (50) in a second axial direction. which is opposite to the first axial direction. The housing volume and channel volume form a volume ratio of approximately 0.0002 <V _Ch <V _C <0.9.

Description

Cross reference to related application

This application is a continuation-in-part of US Application No. 13 / 461,035, filed May 1, 2012, the disclosure of which is incorporated herein by reference in its entirety.

Background of the Revelation

The subject matter disclosed herein relates to the field of turbomachinery, and more particularly to a gas turbine engine having a countercurrent cooling system.

Many turbomachines include a compressor section connected to a turbine section by a common compressor / turbine shaft or rotor and a combustor assembly. The compressor section directs a compressed airflow through a number of successive stages to the combustor assembly. In the combustor assembly, the compressed airflow mixes with a fuel to form a combustible mixture. The combustible mixture is combusted in the combustor assembly to form hot gases. The hot gases are directed to the turbine section through a transition piece. The hot gases expand through the turbine section while rotationally driving turbine blades to produce work that is output, for example, to power a generator, pump, or power a vehicle. In addition to providing compressed air for combustion, a portion of the compressed airflow is directed through the turbine section for cooling.

Brief description of the disclosure

In one aspect of the exemplary embodiment, a gas turbine engine includes a housing assembly surrounding a portion of the gas turbine engine. The housing assembly includes an inner housing portion forming a housing volume V _C and a countercurrent cooling system. The countercurrent cooling system includes a plurality of channels that together form a channel volume V _Ch . The plurality of channels are configured and arranged to direct cooling fluid through the housing assembly in a first axial direction and return the cooling fluid through the housing assembly in a second axial direction opposite the first axial direction. The housing volume and channel volume form a volume ratio of about 0.0002 <V _Ch / V _C <0.9.

In the gas turbine engine, the plurality of channel sections may include a first channel section extending axially through the housing assembly, a second channel section spaced from the first channel section and extending substantially parallel to the first channel section and including at least one cross-flow channel and second channel sections together. The at least one cross-flow channel may include a flow diverting section. The current deflection section may have a curved surface.

In the gas turbine engine, the at least one cross-flow channel may include a first cross-flow channel and a second cross-flow channel, wherein both the first and second cross-flow channels interconnect the first and second channel sections.

The gas turbine engine may include an intersection channel fluidly interconnecting the first and second cross-flow channels.

In the gas turbine engine, the housing assembly may include an outer housing portion and an inner housing portion, with the countercurrent cooling system disposed within the inner housing portion.

In the gas turbine engine, the inner housing portion may include a plurality of shroud retaining members, the countercurrent cooling system extending through at least two of the plurality of shroud retaining members.

The gas turbine engine may include a cooling fluid supply line fluidly connected to the countercurrent cooling system, the cooling fluid supply line including a cooling fluid supply valve selectively actuated to supply cooling fluid to the countercurrent cooling system. In addition, the gas turbine engine may further include a cooling fluid supply valve bypass passage connected in parallel with the cooling fluid supply valve, the cooling fluid supply valve bypass passage configured and arranged to allow a quantity of cooling fluid to flow through the countercurrent cooling system when the cooling fluid supply valve is closed. Additionally or alternatively, the gas turbine engine may further include control means operatively connected to the cooling fluid supply valve, the control means being arranged and arranged to selectively open the cooling fluid supply valve to deliver a quantity of cooling fluid into the countercurrent cooling system.

In the gas turbine engine, the countercurrent cooling system may be located within a turbomachinery section.

The gas turbine engine may include an external heat exchanger fluidly connected to the countercurrent cooling system.

The volume ratio may be about 0.01 <V _Ch / V _C <0.74.

In another aspect of the exemplary embodiment, a method of providing cooling fluid through a gas turbine engine includes directing cooling fluid into a housing assembly of the turbine section of the gas turbine engine. The housing assembly includes an inner housing portion defining a housing volume V _C. The method also includes directing the cooling fluid into a first channel portion extending axially through the housing assembly in a first direction, directing the cooling fluid through a cross-flow channel fluidly coupled to the first channel portion, in a second direction, delivering the Cooling fluid from the cross-flow channel in a second channel portion which extends substantially parallel to the first channel portion, a. The first channel portion, the countercurrent channel and the second channel portion define a channel volume V _Ch . The cooling fluid is directed through the second channel portion in a third direction that is substantially opposite the first direction. The housing volume and channel volume define a volume ratio of about 0.0002 <V _Ch <V _C <0.9.

In the method, directing the cooling fluid into the housing assembly may include directing the cooling fluid into an inner housing portion of the housing assembly.

In the method, directing the cooling fluid through the first channel portion may include directing the cooling fluid through at least two shroud retaining members.

In the method, directing the cooling fluid into the housing assembly may include opening a cooling fluid supply valve. The method may further include flowing the cooling fluid delivery valve with an amount of cooling fluid when the cooling fluid supply valve is closed to maintain a reflux margin within a nozzle of the turbine section.

The method may include directing a portion of the cooling fluid from the one of the first and second channel sections and the crossflow channel into a nozzle of the turbine section.

In the method, directing a cooling fluid into the housing assembly may include supplying the cooling fluid from a compressor section removal into a turbine section of the gas turbine engine.

In the method, directing a cooling fluid into the housing assembly may include supplying the cooling fluid into a housing assembly that houses a compressor section of the gas turbine engine.

In the method, directing the cooling fluid into the housing assembly may include passing the cooling fluid from an external heat exchanger into the housing assembly.

In accordance with yet another aspect of the exemplary embodiment, a gas turbine engine includes a compressor section, a combustor assembly fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor assembly and mechanically connected to the compressor section. One of the compressor and turbine sections includes a housing assembly having an inner housing portion defining a housing volume V _C. The countercurrent cooling system is disposed in one of the compressor and turbine sections. The counterflow cooling system includes a plurality of channels that together define a channel volume V _Ch . The plurality of channels are configured and arranged to direct the cooling fluid through the housing assembly in a first axial direction and to return cooling fluid through the housing assembly in a second axial direction opposite the first axial direction. The housing volume and channel volume form a volume ratio of about 0.0002 <V _Ch / V _C <0.9.

In the gas turbine engine, the countercurrent cooling system may include a first channel portion extending axially through the housing assembly, a second channel portion spaced from and substantially parallel to the first channel portion, and a cross-flow channel interconnecting the first and second channel portions combines.

In the gas turbine engine, the crossflow channel may include a flow diverter section.

In the gas turbine engine, the flow diverting section may include a curved surface.

In the gas turbine engine, the housing assembly may include an outer housing portion and an inner housing portion, with the countercurrent cooling system disposed within the inner housing portion.

The gas turbine engine may include a cooling fluid supply line fluidly connected to the countercurrent cooling system, the cooling fluid supply line including a cooling fluid supply valve selectively operated to supply cooling fluid to the countercurrent cooling system; and a controller operatively connected to the cooling fluid supply valve, the controller being configured and arranged to selectively open the cooling fluid supply valve to deliver a quantity of cooling fluid into the countercurrent cooling system.

In the gas turbine engine, the counterflow cooling system may be disposed in the turbine section.

The gas turbine engine may include an external heat exchanger fluidly connected to the countercurrent cooling system.

In the gas turbine engine, the volume ratio may be about 0.01 <V _Ch / V _C <0.74.

These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.

Brief description of the drawings

The object contemplated as the invention is pointed out with particularity in the claims and clearly claimed in the claims at the end of the description. The foregoing and other features and advantages of the invention will be apparent from the following detailed description taken in conjunction with the accompanying drawings, in which:

1 FIG. 3 is a schematic view of a gas turbine engine with a turbine section having a countercurrent cooling system in accordance with an exemplary embodiment; FIG.

2 a partial, cross-sectional view of the turbine section of the gas turbine engines of 1 is;

3 Figure 3 is a partial, perspective view of the countercurrent cooling system in accordance with an aspect of the exemplary embodiment;

4 a planar view of the countercurrent cooling system according to 3 which illustrates a current redirecting section in accordance with an aspect of the exemplary embodiment;

5 Figure 5 is a side view of a cross-flow channel in accordance with an aspect of the exemplary embodiment;

6 an end view of the cross-flow channel of 5 is;

7 a planar view of the countercurrent cooling system of 3 which includes a current redirecting section in accordance with another aspect of the exemplary embodiment; and

8th Figure 12 is a plan view of the countercurrent cooling system in accordance with another aspect of the exemplary embodiment.

The detailed description exemplifies embodiments of the invention together with advantages and features with reference to the drawings.

Detailed description of the disclosure

With reference to the 1 and 2 For example, a gas turbine engine in accordance with an exemplary embodiment will generally be included 2 shown. The turbo machine 2 closes a compressor section 4 and a turbine section 6 one. The compressor section 4 is fluid with the turbine section 6 through a combustion chamber assembly 8th connected. The combustion chamber assembly 8th includes a variety of combustion chambers, in which one at 10 is shown. The combustion chamber 10 can be in a sleeve-ring arrangement around the turbomachine 2 be arranged. It should be understood, of course, that other arrangements of combustion chambers 10 can also be used. compressor section 4 is also mechanical with the turbine section 6 through a common compressor / turbine shaft 12 connected. There are also withdrawals that may be taken from different compressor stages and which are fluidly connected to turbine components without passing through the combustion chamber 10 to step. These withdrawals are used to cool turbine components as well as shrouds and nozzles on the stator along with vanes, discs and spacers on the rotor.

The turbine section 6 closes a housing 18 one that has a variety of turbine stages 25 encloses. The turbine stages 25 close a first turbine stage 26 , a second turbine stage 27 . a third turbine stage 28 and a fourth turbine stage 29 one. The first turbine stage 26 includes a variety of vanes or nozzles 33 and a plurality of rotating components in the form of blades or blades 34 one. The shovels 34 are attached to a first rotor part (not shown) connected to the shaft 12 is coupled. The second turbine stage 27 includes a second plurality of blades or nozzles 37 and a second plurality of blades or blades 38 one. The shovels 38 are coupled to a second rotor part (not shown). The third turbine stage 28 includes a third plurality of blades or nozzles 41 and a second plurality of blades or blades 42 which are coupled to a third rotor part (not shown). The fourth turbine stage 29 includes a fourth plurality of blades or nozzles 45 and a fourth plurality of blades or blades 46 which are coupled to a fourth rotor part (not shown). It should of course be understood that the number of turbine stages may be different.

The housing 18 closes a housing assembly 50 with an outer housing section 60 and an inner housing portion 64 one. A stop shoulder 65 extends from the outer housing portion 60 to the inner housing section 64 , The stop shoulder 65 limits the axial movement of the inner housing portion 64 during operation of the turbomachine 2 , A first room zone 67 is between the outer housing section 60 and the inner housing section 64 upstream of the stop shoulder 65 educated. A second room zone 69 is between the outer housing section 60 and the inner housing section 64 downstream of the stop shoulder 65 educated. The first and second room zones 67 and 69 are fluidly connected to one or more compressor draws (not shown). The inner housing section 64 closes a lead 75 one with the stop shoulder 65 can come into contact and a variety of shroud retaining elements 80 - 83 , Each shroud retaining element 80 - 83 includes a pair of hook elements, as in 84 shown on the shroud retaining element 80 including a corresponding plurality of stationary shroud elements 86 - 89 hold. The shroud elements 86 - 89 Make a desired distance between the inner housing section 64 and associated tip portions (not separately indicated) of blades 34 . 38 . 42 and 46 ready. In many cases, shroud elements close 86 - 89 various sealing components that the working fluid against overflow of the tip portions of the blades 34 . 38 . 42 and 46 limit.

In accordance with an exemplary embodiment, the turbomachine completes 2 a countercurrent cooling system 100 in the inner housing section 64 is provided. How best in the 3 and 4 shown closes the countercurrent cooling system 100 a first channel section 108 in fluidly communicating with a second channel section 109 through a cross-flow channel 111 connected to a Stromumlenkungskappe or section 112 with a substantially linear inner surface 113 having. First and second channel sections 108 and 109 extend axially through inner housing sections 64 , In addition, a first channel section extends 108 substantially parallel to the second channel section 109 within the inner housing section 64 , The passage of cooling flow through the channel sections 108 and 109 , which are arranged in the manner as described above, reduces circumferential thermal gradients within the inner housing portion 64 , In addition, a deep convection flow reduces within the inner housing section 64 passes, thermal gradients in the shroud retaining elements 80 - 83 , The passage of cooling flow through the channel sections 108 and 109 In this particular way, the average temperature reduces a plurality of turbine stages 25 to draw a desired benefit from the distance.

The first channel section 108 closes a first end section 114 a, leading to a second end section 115 through an intermediate section 116 extends. The first end section 114 sets an input section 118 fixed, the flow with the second room zone 69 is connected while the second end portion 115 with the crossflow channel 111 connected is. The second channel section 109 closes a first section 127 a, extending from the cross-flow channel 111 to a second end portion 128 through an intermediate section 129 extends. The second end section 128 is to an output channel section 130 coupled, which has an outlet section 131 having. The outlet section 131 leads through the inner housing section 64 and is fluid with the one or more of the blades 33 . 37 . 41 and 45 connected. The cooling fluid passes from a compressor discharge (not shown) to the second space zone 69 one. The cooling fluid flows into the inlet section 118 and along the first channel section 108 , The cooling fluid then enters the crossflow channel 111 one and is about the essentially straight inner surface 113 of the power diverting section 112 in the second channel section 109 prior to entering and providing refrigeration for these, the third plurality of nozzles 41 directed. Passing cooling fluid through the first channel section 108 in a first direction and through the second channel section 109 in a second, opposite direction creates a counterflow within the inner housing portion 64 , In accordance with an aspect of the exemplary embodiment, which is disclosed in US the 5 and 6 is illustrated, the cross-flow channel 111 with an enlarged cavity area 140 and with an outlet plate 145 Be equipped with a variety of openings 147 having a desired pressure drop between the cooling flow, the second end portion 115 of the first channel section 108 leaves, and cooling fluid, in the first end portion 127 of the second channel section 109 enter, create.

In accordance with one aspect of an exemplary embodiment, the inner housing portion defines 64 a housing volume V _C firmly. In further accordance with an exemplary embodiment, the first channel portion 108 , the second channel section 109 and the crossflow channel 111 together a channel volume V _Ch fixed. In accordance with aspects of an exemplary embodiment, the housing volume V _C and the channel volume V _{Ch form} a volume ratio of about 0.0002 <V _Ch / V _C <0.9. In accordance with another aspect of an exemplary embodiment, the housing volume V _C and the channel volume V _{Ch forms} a volume ratio of about 0.01 <V _Ch / V _C <0.74. The volume ratio provides a desired cooling for the inner housing section 64 and a desired clearance gap over the tip portions of the rotating components, which is a desired operating efficiency of the turbomachine 2 can maintain. The thermal mass of the inner housing section 64 can be adjusted by changing the channel volume V _Ch , with a relatively lower thermal mass of the housing being set by a relatively higher channel volume V _ch . A relatively lower thermal mass of the housing may allow the housing to expand or contract radially more rapidly during transient operation. This may allow the housing expansion or contraction to better conform to the expansion or contraction of the rotating component, thereby maintaining a desired clearance gap. The aforementioned ratios of V _Ch / V _C can provide the desired characteristic of thermal expansion or contraction of the housing.

The counterflow reduces circumferential thermal gradients within the inner housing section 64 by providing heat transfer between the cooling stream passing through the first channel section 108 occurs and the cooling flow through the second channel section 109 occurs. Also provides the embedded countercurrent cooling system 100 within the inner housing section 64 deep convection cooling, which reduces thermal gradients present in shroud retaining elements 80 - 83 can occur and that the average temperatures of the variety of turbine stages 25 reduced, which creates a desired benefit from a distance. At this point, it should be understood that the counterflow channel 111 with a power diverter cap or section 148 can be provided which has a substantially curved surface 149 has, as in 7 shown, wherein like reference numerals represent corresponding parts in the respective views. The essentially curved surface 149 can be adjusted, a desired flow characteristics within the countercurrent cooling system 100 to accomplish.

In accordance with one aspect of the exemplary embodiment, the turbomachine completes 2 a cooling fluid supply line 150 in fluid communication with the second room zone 69 connected is. The cooling fluid supply line 150 closes an inlet 151 which is fluidly connected to a compressor discharge (not shown). The cooling fluid supply line 150 is also a cooling fluid supply valve 157 and a cooling fluid supply valve bypass passage 160 having shown. The cooling fluid supply valve bypass line 160 includes a metering flow orifice (not separately labeled) that allows the cooling fluid to enter the second space zone 69 when the cooling fluid supply valve 157 closed is. In this way, the cooling fluid supply valve bypass line is maintained 160 desired reflux pressure spans within the third plurality of nozzles 41 upright. In further accordance with the exemplary aspect, the cooling fluid supply valve 157 effective with a controller 164 connected. The control device 164 is also coupled to various temperature sensors (not shown). The control device 164 opens the cooling fluid supply valve 157 selected to a desired flow of cooling fluid in the second space zone 69 allow.

The amount of cooling fluid entering the second space zone 69 occurs and, more specifically, in the countercurrent cooling system 100 , may be used to provide clearance between tip portions (not separately labeled) of blades 34 . 38 . 42 and 46 and corresponding ones of the shroud elements 86 - 89 to control. More specific are during the starting phase of the turbomachine 2 Spaces between tip portions (not separately labeled) of the blades 34 . 38 . 42 and 46 and corresponding ones of the shroud elements 86 - 89 bigger than when the turbomachine 2 running at full speed and at full speed-full load operation. Between the starting phase and the full speed and between the full speed and the full speed-full load operation, rotating components of the turbomachine expand 2 at a rate that's faster than one Expansion rate of stationary components, such as the inner housing section 64 and shroud elements 86 - 89 , is. Various rates of thermal expansion lead to undesirable distances between the rotating and stationary components. Controlling fluid flow into the countercurrent cooling system 100 equalizes expansion rates of rotating components and stationary components more while the turbomachinery 2 between operating conditions in the starting phase and the phase at full speed and between the phase at full speed and the phase at full speed and full load passes. Adjusting the expansion rates of the rotating components and the stationary components provides closer clearance gaps in transient and steady state turbomachinery operation 2 ready. The narrower clearance gaps result in a reduction in working fluid losses over tip portions of the rotating components, which improves the performance and efficiency of the turbomachine 2 improved.

A countercurrent cooling system in accordance with another aspect of the exemplary embodiment is generally included 175 in 8th shown. The countercurrent cooling system 175 closes a first channel section 180 with a first end portion 182 a, leading to a second end section 183 through an intermediate section 184 extends. The countercurrent cooling system 175 also includes a second channel section 190 a, which is substantially parallel to the first channel section 180 within the inner housing section 64 extends. The second channel section 190 closes a first end section 192 a, leading to a second end section 193 through an intermediate section 194 extends. The second end section 193 is fluid with an output channel 196 connected in fluid communication with the third plurality of nozzles 41 communicates.

The first channel section 180 is with the second channel section 190 through a first cross-flow channel 204 and a second cross-flow channel 207 connected. The first cross-flow channel 204 closes a first inlet 210 a, which is fluidly with the intermediate section 184 of the first channel section 180 and a first outlet 211 coupled in fluid communication with the first end portion 192 of the second channel section 190 connected is. The second cross-flow channel 207 closes a second inlet 214 in fluidly with the second end portion 183 of the first channel section 180 and a second outlet 215 fluidly connected to an intermediate section 194 of the second channel section 190 connected is. The first cross-flow channel 204 is with the second cross-flow channel 207 through a crossing canal 220 connected. The crossing canal 220 creates a mixing zone 225 for cooling fluid passing through the first cross-flow channel 204 and the second crossflow channel 207 occurs. The mixing zone 225 assists in matching temperatures of the cooling fluid passing through the first crossflow channel 204 and the second crossflow channel 207 occurs to thermal gradients within the inner housing section 64 to reduce what are thermal gradients and mean temperatures in the countercurrent cooling system 175 reduced.

At this point, it should be understood that the exemplary embodiment provides a countercurrent cooling system for reducing mean metal temperatures and thermal gradients within a turbomachine section of a turbomachine. This system also provides deep convection cooling for stationary components as well as inner casings, shroud elements and the like arranged along a gas path of the turbine. In this way, the countercurrent cooling system can more closely tune or equalize the thermal expansion of stationary turbine components and rotating turbine components. In addition, cooling flow through the countercurrent cooling system may be selectively controlled to adjust the thermal expansion rates of the stationary components and the rotating components in the various phases of operation of the turbine. The approximation of thermal expansion rates reduces spacing gaps between the stationary components and the rotating components, especially during the transition from one operating phase to another phase of operation. The reduction of gap gaps results in a reduction of working fluid losses along the hot gas path, which improves performance and efficiency.

It is understood that according to various embodiments, one or more countercurrent cooling systems described herein may be configured as a passive proximity control system. By "passive" it should be understood that distances can be autonomously adjusted based only on turbo machine operating parameters without any intervention from external programmed control systems and / or personnel.

It should also be understood that while it is with the turbine section 6 is described together, a countercurrent cooling system 300 also in the compressor section 4 can be integrated to intervals for compressor stages 310 to improve. It should be further understood that the countercurrent cooling system 300 in accordance with the exemplary embodiments with external heat exchangers 320 and 330 can be coupled, the flow with the compressor section 4 and the turbine section 6 are connected. External heat exchangers 320 and 330 may also be fluidly coupled to one another in accordance with an aspect of the exemplary embodiment to provide cooling flow from the compressor section 4 to the countercurrent cooling system 300 in the turbine section 6 to lead. In accordance with one aspect of the exemplary embodiment, the countercurrent cooling system could 300 Gases from an upstream portion (behind, for example, a sixth stage) (not separately labeled) of the compressor section 4 Extract the gases through the external heat exchanger 320 and then a housing portion (not separately provided with reference numerals) of the compressor section 4 and on the turbine section 6 conduct. The gases passing through the compressor section 4 will improve the uniformity of thermal expansion, allowing developers to apply tighter tip pitch tolerances to improve compressor efficiency. The presence of one or more external heat exchangers provides additional conditioning of the cooling flow to the distance control with the turbomachine 2 continue to improve.

The term "about" is intended to include an amount of error assigned to a measurement of a particular size based on the equipment available at the time of filing the application. For example, "about" may include a range of +/- 8% or 5% or 2% of a given value.

The terminology used herein for the purpose of describing only specific embodiments is not intended to limit the disclosure. As used herein, the singular forms "a" and "the", "the", "the" are also intended to include the plural forms unless the context indicates otherwise. It will further be understood that the terms "pointing at" and / or "having" as used in this specification indicate the presence of the specified features, numbers, steps, operations, elements and / or components, but not the Preclude the presence or addition of one or more other elements, numbers, steps, modes, components, and / or groups thereof.

While the disclosure is provided in detail in connection with only a limited number of embodiments, it should be readily understood that the disclosure is not limited to such disclosed embodiments. Rather, the disclosure may be modified to encompass any number of variations, changes, substitutions, or equivalent arrangements, not previously described, but which are consistent with the spirit and scope of the disclosure. In addition, it should be understood that while various embodiments of the disclosure have been described, the exemplary embodiment or embodiments may include only some of the described exemplary aspects. Accordingly, the disclosure should not be construed as limited by the above description, but is limited only by the scope of the appended claims.

A gas turbine machine 2 closes a housing assembly 50 one that has a section of the gas turbine engine 2 surrounds. The housing assembly 50 closes an inner housing section 64 defining a housing volume V _C and a countercurrent cooling system 100 one inside the inner housing section 64 is arranged. The countercurrent cooling system 100 includes a variety of channels 111 . 196 . 204 . 207 . 220 which together define a channel volume V _Ch . The variety of channels 111 . 196 . 204 . 207 . 220 is configured and arranged, cooling fluid through the housing assembly 50 in a first axial direction and cooling fluid through the housing assembly 50 in a second axial direction, which is opposite to the first axial direction. The housing volume and channel volume form a volume ratio of approximately 0.0002 <V _Ch <V _C <0.9.

LIST OF REFERENCE NUMBERS

2

 turbomachinery

4

 compressor section

6

 turbine section

8th

 combustion chamber assembly

10

 combustors

12

 common compressor / turbine shaft

18

 casing

25

 turbine stages

26

 first turbine stage

27

 second turbine stage

28

 third turbine stage

29

 fourth turbine stage

33

 Variety of wings or nozzles

34

 shovel

37

 Variety of wings or nozzles

38

 second variety of leaves or blades

41

 third variety of wings or nozzles

42

 second variety of leaves or blades

45

 fourth variety of wings or nozzles

46

 fourth variety of leaves or shovels

50

 housing assembly

60

 outer housing section

64

 inner housing section

65

stop shoulder

67

 first room zone

69

 second room zone

75

 head Start

80

 Shroud retaining element

81

 Shroud retaining element

82

 Shroud retaining element

83

 Shroud retaining element

84

 hook element

86

 stationary shroud element

87

 stationary shroud element

88

 stationary shroud element

89

 stationary shroud element

100

 Reverse flow cooling system

108

 first channel section

109

 second channel section

111

 first crossflow channel

112

 River diversion cap or section

113

 essentially straight inner surface

114

 first end section

115

 second end section

116

 intermediate section

118

 inlet section

127

 first end section

128

 second end section

129

 intermediate section

130

 Exit channel section

131

 outlet

140

 cavity region

145

 Ausströmplatte

147

 Variety of openings

148

 Power diverter cap or element

149

 essentially curved surface

150

 Cooling fluid supply line

151

 inlet

157

 Cooling fluid supply valve

160

 Kühlfluidversorgungsventilumströmungsleitung

164

 control device

175

 Reverse flow cooling system

180

 first channel section

182

 first end section

183

 second end section

184

 intermediate section

190

 second channel section

192

 first end section

193

 second end section

194

 intermediate section

196

 exhaust port

204

 Cross-flow channel

207

 second cross-flow channel

210

 first inlet

211

 first outlet

214

 second inlet

215

 second outlet

220

 crossover passage

225

 mixing zone

300

 cooling system

310

 compressor stages

320

 heat exchangers

330

 heat exchangers

Claims (10)

Gas turbine machine ( 2 ) comprising: a housing assembly ( 50 ) surrounding a portion of the gas turbine engine, the housing assembly ( 50 ) an inner housing section ( 64 ) defining a housing volume V _C ; and a countercurrent cooling system ( 100 ), which within the inner housing section ( 64 ), wherein the countercurrent cooling system ( 100 ) a plurality of channels ( 108 . 109 . 180 . 190 ), which together form a channel volume V _Ch , wherein the plurality of channels ( 108 . 109 . 180 . 190 ) is arranged and arranged, cooling fluid through the housing assembly ( 50 ) in a first axial direction and cooling fluid through the housing assembly ( 50 ) in a second axial direction opposite the first axial direction, wherein the housing volume and the channel volume form a volume ratio of about 0.0002 <V _Ch / V _C <0.9. Gas turbine machine ( 2 ) according to claim 1, wherein said plurality of channel sections ( 108 . 109 . 180 . 190 ) a first channel section ( 108 . 180 ) extending axially through the housing assembly ( 50 ), a second channel section ( 109 . 190 ) spaced from the first channel section (FIG. 108 . 180 ) and extends substantially parallel thereto, and at least one cross-flow channel ( 111 . 204 . 207 ) comprising the first and second channel sections ( 108 . 109 ) connects. Gas turbine machine ( 2 ) according to claim 2, wherein the at least one cross-flow channel ( 111 . 204 . 207 ) includes a current redirecting section. Gas turbine machine ( 2 ) according to claim 3, wherein the current deflection section has a curved surface ( 149 ). Gas turbine machine ( 2 ) according to claim 2, wherein the at least one cross-flow channel ( 111 . 204 . 207 ) a first cross-flow channel ( 111 ) and a second cross-flow channel ( 207 ), wherein each of the first and second cross-flow channels ( 111 . 207 ) the first and second channel sections ( 108 . 109 . 180 . 190 ) connects. Gas turbine machine ( 2 ) according to claim 5, further comprising: a crossing channel ( 220 ), the first and the second cross-flow channel ( 111 . 207 ) fluidly interconnects. Gas turbine machine ( 2 ) according to claim 1, wherein the housing assembly ( 50 ) an outer housing section ( 60 ) and an inner housing section ( 64 ), wherein the countercurrent cooling system ( 100 ) within the inner housing section ( 64 ) is arranged. Gas turbine machine ( 2 ) according to claim 7, wherein the inner housing section ( 64 ) a plurality of shroud retaining elements ( 80 . 81 . 82 . 83 ), wherein the countercurrent cooling system ( 100 ) by at least two of the plurality of shroud retaining elements ( 80 . 81 . 82 . 83 ). Method for supplying cooling fluid through a gas turbine engine ( 2 ), the method comprising: passing cooling fluid into a housing assembly ( 50 ) of the gas turbine engine ( 2 ), wherein the housing assembly ( 50 ) an inner housing section ( 64 ) defining a housing volume V _C ; Directing the cooling fluid into a first channel section ( 108 ) extending axially through the housing assembly ( 50 ) extends in a first direction; Passing the cooling fluid through a cross-flow channel ( 111 . 204 . 207 ), which is in fluid communication with the first channel section ( 108 ) is coupled, in a second direction; Supplying the cooling fluid from the crossflow channel ( 111 . 204 . 207 ) into a second channel section ( 109 ) substantially parallel to the first channel section (FIG. 108 ), wherein the first channel section ( 108 ), the crossflow channel ( 204 ) and the second channel section ( 109 ) form a channel volume V _Ch ; and passing the cooling fluid through the second channel section (FIG. 109 ) in a third direction that is substantially opposite the first direction, wherein the housing volume and the channel volume form a volume ratio of approximately 0.0002 <V _Ch / V _C <0.9. Gas turbine machine ( 2 ), comprising: a compressor section ( 4 ); a combustion chamber assembly ( 8th ) in fluid communication with the compressor section ( 4 ) connected is; and a turbine section ( 6 ) in fluid communication with the combustor assembly ( 8th ) and mechanically with the compressor section ( 4 ), one of the compressors ( 4 ) and turbine sections ( 6 ) a housing assembly ( 50 ), which has an inner housing section ( 64 ) defining a housing volume V _C ; and a countercurrent cooling system ( 100 ), which is in one of the compressor ( 4 ) and turbine sections ( 6 ), wherein the countercurrent cooling system ( 100 ) a plurality of channels ( 108 . 109 . 180 . 190 ), which together form a channel volume V _Ch , wherein the plurality of channels ( 108 . 109 . 180 . 190 ) is arranged and arranged, cooling fluid through the housing assembly ( 50 ) in a first axial direction and cooling fluid through the housing assembly ( 50 ) in a second axial direction opposite the first axial direction, wherein the housing volume and the channel volume form a volume ratio of about 0.0002 <V _Ch / V _C <0.9.

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