CA2091231A1 - Compressor group - Google Patents
Compressor groupInfo
- Publication number
- CA2091231A1 CA2091231A1 CA 2091231 CA2091231A CA2091231A1 CA 2091231 A1 CA2091231 A1 CA 2091231A1 CA 2091231 CA2091231 CA 2091231 CA 2091231 A CA2091231 A CA 2091231A CA 2091231 A1 CA2091231 A1 CA 2091231A1
- Authority
- CA
- Canada
- Prior art keywords
- water
- intercooler
- compressor group
- flow direction
- compression stage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
- F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
In a compressor group of a gas turbine group, the intercooling of the air pre-compressed in a first com-pression stage (4) is undertaken in an intercooler which is placed within the stator casing (2) and in the flow direction of the compression stages. This inter-cooler has the shape of a double-cone device (5), water (6) being sprayed as cooling medium into the internal space (13) of this device (5) where it is mixed with the pre-compressed air (16). The cooling takes place by evaporation of the water (6) sprayed in. Connecting conduits to an intercooler placed outside the stator casing (2) and from the intercooler to the stator cas-ing (2) are no longer necessary.
(Fig. 1)
In a compressor group of a gas turbine group, the intercooling of the air pre-compressed in a first com-pression stage (4) is undertaken in an intercooler which is placed within the stator casing (2) and in the flow direction of the compression stages. This inter-cooler has the shape of a double-cone device (5), water (6) being sprayed as cooling medium into the internal space (13) of this device (5) where it is mixed with the pre-compressed air (16). The cooling takes place by evaporation of the water (6) sprayed in. Connecting conduits to an intercooler placed outside the stator casing (2) and from the intercooler to the stator cas-ing (2) are no longer necessary.
(Fig. 1)
Description
2~n, ~23~
E~o 12 . 3 . 1992 92/031 Compressor group BACKGROUND OF THE INVENTION
Field of the Invention The present invention relates to a compressor group in accordance with the preamble to claim 1. It also relates to a method for operating such a com-pressor group.
Discussion of Backqround It is generally known that the power taken by a compressor can be significantly reduced, for a given ~inal pressure, if the medium, i.e. air in the case of gas turbine groups is re-cooled at least once during the compression. For this purpose, the pre-compressed air flows, after a first compression stage, via an outlet flow conduit into an intercooler in which, by heat exchange, cooling of the pre-compressed air takes place, whereupon the air cooled in this manner is led back via an inlet flow conduit to the second compression stage. It is obvious that in this con~iguration, which is associated with the general state o~ the art, a high level of installation compli-cation must be operated and this has not unsubstantial effects on the installation costs.
SUMM~RY OF THE INVENTION
Accordingly, one object of this invention, as claimed, is to obviate the disadvantages cited above in a compressor group of the type mentioned at the beginning.
The essential advantage of the invention may be seen in the fact that a device otherwise used as a pre-mixed burner i8 used as an evaporative intercooler.
g2/031 ~
The device employed in this case is the so-called "double-cone burner", as has become known from EP-0321809. The cooling of the compressor medium, pre-compressed air therefore in gas turbine groups, takes place by means of evaporation of the water sprayed into this device for cooling purposes.
The advantages of this "double-cone device" are also fully effective in this new type of applica-tion.
The partial pressure of the water as the cooling medium can, in fact, be controlled by means of the water temperature before injection; it should, however, be mentioned that this effect is small.
A further advantage of the invention may be seen in the fact that the selected arrangement, placing the device in the outlet flow and inlet flow axes, respec-tively, of the two compression stages can, with minimum pressure drop, compensate for the smallest temperature differences in the wake of the double-cone configur~
ation because of the vortex structure, i.e. the so-called "pattern factor" can be extinguished. In this double-cone device itself, hot streaks are held in the centrifugal field and in the revexse flow region of the "vortex breakdown" until the temperature of the core flow has fallen to the surrounding temperature downstream.
A further advantage of the invention consists in the fact that with an annular arrangement o the double-cone configuration, the possibility e~ists of providing an intermediate bearing by means of support ribs in the heat exchanger zone, in order to reduce the clearance in the compressor.
Advantageous and expedient further developments of the solution in the invention are given in the further claims.
BRIEF DBSCRIPTION OF THE DRAWINGS
A more complete appreciation of the invention and many of the attendant advantages thereof will be 3 2 ~3 ~
readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings of an embodiment of the invention wherein:
Fig. 1 shows a double-cone device connected between two compression stages of a compressor group, Fig. 2 shows a double-cone device in perspecti~e view, appropriately sectioned and O Fig. 3 shows a section through the double-cone device of Fig. 2 in the plane III-III.
DESCRIPTION OF THE PREFERRED EMB DIMENTS
Referring now to the drawings, wherein all the elements not necessary for understanding the invention are omitted, wherein the flow direction of the media are indicated by arrows and wherein like reference numerals designate identical or corresponding parts throughout the several views, Fig. 1 shows a compressor group of a gas turbine group, essentially comprising a rotor l, a stator 2 and two compression stages 4 and 8.
The induced air 3 is pre-compressed in a first stage 4, which operates as the low pressure compressor. After passing through this pre-compression stage 4, this air 16 is led into an intermediary annular chamber 10 integrated in the stator 2 between the two compression stages 4, 8 instead o~ the conventional intercooling, in which the air is led through a heat exchanger acting outside the compressor group. This annular chamber 10 is equipped with a numker, to suit the process, of double-cone devices 5, which are placed on the periphery of the annular chamber lOo The final purpose of this configuration consists in leading the air 16 coming from the low-pressure compressor 4 through the said double-cone devices 5, before it is introduced into the second compression stage 8 designed as the high-pressure compressor. After the air 9 has been completely compressed, it is, in the normal case, thermally treated in a combustion chamber (not shown). 2 ~ ~ ~ 2 In the case of the seiected arrangement of an annular chamber lO, the possibility QXiStS of installing an intermediate bearing 7 by means, for example, of sup-port ribs in the region of the double-cone device 5 in order to reduce the clearance in the compressor group~
The mode of operation of the double-cone device 5 men-tioned is considered in more detail further below. The diagrammatic representation from Fig. 1 is itself suf-ficient to show very clearly the compact nature of thesolution proposed. The re-cooling of the air com-pressed in the low-pre5sure compressor 4 for the pur-pose of reducing the power taken by the compressor group overall, for a given final pressure, takes place within the stator 2 and immediately downstream of the first compression stage 4 and upstream of the second compression stage 8 so that conduit penetrations through the stator to and from a heat exchanger acting - outside the compressor group are no longer-necessary.
It should first be noted that the double-cone device 5 is supplied with water 6, arrangements being, of course, provided at the end of this device to separate the possibly incompletely evaporated water. This is done by means of the centrifugal effect which is present at the end of the device due to the mode of operation of the double-cone device 5 and by means of further suitable measures. The cooling of the pre-compressed air 16 therefore takes place by means of the evaporation of at least part of the water 6 injected into the double-cone device 5. The partial pressure of the water can be controlled by the water temperature before injection, as has already been thoroughly explained further above. The vortex structure of the double-cone device 5 itself ensures that compensation can be provided for the smallest temperature differ-ences with minimum pressure drop. The operational pro-cess of the double-cone device 5 also permits possible hot streaks to be retained in the centrifugal field and 2 ~ 3 ~
in the reverse flow region of the reverse flow zone forming at the outlet from the burner (vortex break-down) until such time as the temperature of the core flow has fallen to the surrounding temperature down-stream.
For better understanding of the construction ofthe device 5, it is advantageous to make use of Fig. 2 and 3 simultaneously. Furthermore, in order to prevent the individual figures becoming unnecessarily compli-cated, partial aspects of this device are distributedbetween the indivldual figures, reference being made to this fact, as needed, during the description of the embodiment example.
The core body of the device 5 shown in Fig. 2 con-sists of two half hollow partial conical bodies 11, 12which are located one upon the other, offset relative to one another. The offset of the respective center lines frees one tangential air inlet slot llc, 12c (Fig. 3) on each of the two sides in an axially symmetrical arrangement. The pre-compressed air 16, already mentioned above, flows through these slots into the internal space 13 of the device 5, i.e. into the conical hollow space. The conical shape of the partial conical bodies 11, 12 shown has a certain constant angle in the flow direction~ The partial conical bodies 11, 12 can, of course, describe an increasing cone angle (convex shape = trumpet shape) or a decreasing cone angle (concave shape = tulip shape) in the flow direction. The two shapes last mentioned are not recorded in the drawing because they can be imagined without difficulty. The shape which is finally used depends on the various parameters of the basic process. The shape shown in the drawing is preferably used. The tangential width of the air inlet slot3 llc, 12c is a dimension which results from the offset between the two center lines llb, 12b (see Fig. 3). The two partial conical bodies 11, 12 each have an initial cylindrical part lla, 12a which, by ~2/~31 analogy with the partial conical ~odies 11, 12, extend 2 offset relative to one another so that the tangential air inlet slots llc~ 12c are present over the whole length of the device 5. The double-cone device 5 can, S of course, be configured to be purely conical, i.e.
without an initial cylindrical part. A nozzle 14, which undertakes water spraying into the internal space 13 of the device 5, is accommodated in this initial cylindrical part. The spraying of water ensures that the pre-compressed air 16, which flows via inlet passages 17a, 17b (see Fig. 3) and through the tangential air inlet slots llc, 12c into the internal space 13 of the device 5, is continuously subjected to a cooling process. The introduction of the water quantity required into the internal space 13 of the device can take place in many ways. As an example, conduits ~not shown) can be provided in the region of the tangential air inlet slots llc, 12c as a support for or as a replacement for the spraying of water at the end, these conduits extending over the complete length of the double-cone device 5 and having, along -their length, a number of openings through which the required water can be introduced. Owing to the tangential flow of the air 16 into the internal space 13 of the device 5, a swirl motion oriented in the axial direction occurs and, because of its nature, this is suitable for producing thorough mixing with the second medium sprayed in (in our case, this is a conical water-spray pattern 15) which evaporates and so causes cooling. It should be noted that the vortex flow has intrinsically little swirl in the center but it has a surplus of axial velocity. Because the swirl rate increases strongly in the axial direction and reaches the critical value, the so-called breakdown value, at the end of the device 5, this provides in each region a vortex reverse flow 20 whose position is stable. This vortex reverse flow 20 ensures that the possibly surplus water, which is sprayed into the 92/0~1 ~ internal space 13 through the nozzle 14 and which, for ~ ~ 7 ~ ~
whatever reason, is not completely evaporated, is ~1 centrifuged out in the vortex plane 21. Other means of centrifuging out the water not evaporated can also be provided, which means are to be placed in the intermediate space la, downstream of the double-cone device 5 and upstream of the high-pressure compressor 8. The termination of the intercooler body is ~o~ned by a wall 19 which forms the inlet front of the annular chamber 10 along which the double-cone devices 5 provided are attached.
I'Obviously, numerous modification3 and variations of the present invention are possible in light of the above teachings. It ls therefore to be understood that within the scope of the appended claims, the invention may be practised otherwise than as specifically described herein."
.
E~o 12 . 3 . 1992 92/031 Compressor group BACKGROUND OF THE INVENTION
Field of the Invention The present invention relates to a compressor group in accordance with the preamble to claim 1. It also relates to a method for operating such a com-pressor group.
Discussion of Backqround It is generally known that the power taken by a compressor can be significantly reduced, for a given ~inal pressure, if the medium, i.e. air in the case of gas turbine groups is re-cooled at least once during the compression. For this purpose, the pre-compressed air flows, after a first compression stage, via an outlet flow conduit into an intercooler in which, by heat exchange, cooling of the pre-compressed air takes place, whereupon the air cooled in this manner is led back via an inlet flow conduit to the second compression stage. It is obvious that in this con~iguration, which is associated with the general state o~ the art, a high level of installation compli-cation must be operated and this has not unsubstantial effects on the installation costs.
SUMM~RY OF THE INVENTION
Accordingly, one object of this invention, as claimed, is to obviate the disadvantages cited above in a compressor group of the type mentioned at the beginning.
The essential advantage of the invention may be seen in the fact that a device otherwise used as a pre-mixed burner i8 used as an evaporative intercooler.
g2/031 ~
The device employed in this case is the so-called "double-cone burner", as has become known from EP-0321809. The cooling of the compressor medium, pre-compressed air therefore in gas turbine groups, takes place by means of evaporation of the water sprayed into this device for cooling purposes.
The advantages of this "double-cone device" are also fully effective in this new type of applica-tion.
The partial pressure of the water as the cooling medium can, in fact, be controlled by means of the water temperature before injection; it should, however, be mentioned that this effect is small.
A further advantage of the invention may be seen in the fact that the selected arrangement, placing the device in the outlet flow and inlet flow axes, respec-tively, of the two compression stages can, with minimum pressure drop, compensate for the smallest temperature differences in the wake of the double-cone configur~
ation because of the vortex structure, i.e. the so-called "pattern factor" can be extinguished. In this double-cone device itself, hot streaks are held in the centrifugal field and in the revexse flow region of the "vortex breakdown" until the temperature of the core flow has fallen to the surrounding temperature downstream.
A further advantage of the invention consists in the fact that with an annular arrangement o the double-cone configuration, the possibility e~ists of providing an intermediate bearing by means of support ribs in the heat exchanger zone, in order to reduce the clearance in the compressor.
Advantageous and expedient further developments of the solution in the invention are given in the further claims.
BRIEF DBSCRIPTION OF THE DRAWINGS
A more complete appreciation of the invention and many of the attendant advantages thereof will be 3 2 ~3 ~
readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings of an embodiment of the invention wherein:
Fig. 1 shows a double-cone device connected between two compression stages of a compressor group, Fig. 2 shows a double-cone device in perspecti~e view, appropriately sectioned and O Fig. 3 shows a section through the double-cone device of Fig. 2 in the plane III-III.
DESCRIPTION OF THE PREFERRED EMB DIMENTS
Referring now to the drawings, wherein all the elements not necessary for understanding the invention are omitted, wherein the flow direction of the media are indicated by arrows and wherein like reference numerals designate identical or corresponding parts throughout the several views, Fig. 1 shows a compressor group of a gas turbine group, essentially comprising a rotor l, a stator 2 and two compression stages 4 and 8.
The induced air 3 is pre-compressed in a first stage 4, which operates as the low pressure compressor. After passing through this pre-compression stage 4, this air 16 is led into an intermediary annular chamber 10 integrated in the stator 2 between the two compression stages 4, 8 instead o~ the conventional intercooling, in which the air is led through a heat exchanger acting outside the compressor group. This annular chamber 10 is equipped with a numker, to suit the process, of double-cone devices 5, which are placed on the periphery of the annular chamber lOo The final purpose of this configuration consists in leading the air 16 coming from the low-pressure compressor 4 through the said double-cone devices 5, before it is introduced into the second compression stage 8 designed as the high-pressure compressor. After the air 9 has been completely compressed, it is, in the normal case, thermally treated in a combustion chamber (not shown). 2 ~ ~ ~ 2 In the case of the seiected arrangement of an annular chamber lO, the possibility QXiStS of installing an intermediate bearing 7 by means, for example, of sup-port ribs in the region of the double-cone device 5 in order to reduce the clearance in the compressor group~
The mode of operation of the double-cone device 5 men-tioned is considered in more detail further below. The diagrammatic representation from Fig. 1 is itself suf-ficient to show very clearly the compact nature of thesolution proposed. The re-cooling of the air com-pressed in the low-pre5sure compressor 4 for the pur-pose of reducing the power taken by the compressor group overall, for a given final pressure, takes place within the stator 2 and immediately downstream of the first compression stage 4 and upstream of the second compression stage 8 so that conduit penetrations through the stator to and from a heat exchanger acting - outside the compressor group are no longer-necessary.
It should first be noted that the double-cone device 5 is supplied with water 6, arrangements being, of course, provided at the end of this device to separate the possibly incompletely evaporated water. This is done by means of the centrifugal effect which is present at the end of the device due to the mode of operation of the double-cone device 5 and by means of further suitable measures. The cooling of the pre-compressed air 16 therefore takes place by means of the evaporation of at least part of the water 6 injected into the double-cone device 5. The partial pressure of the water can be controlled by the water temperature before injection, as has already been thoroughly explained further above. The vortex structure of the double-cone device 5 itself ensures that compensation can be provided for the smallest temperature differ-ences with minimum pressure drop. The operational pro-cess of the double-cone device 5 also permits possible hot streaks to be retained in the centrifugal field and 2 ~ 3 ~
in the reverse flow region of the reverse flow zone forming at the outlet from the burner (vortex break-down) until such time as the temperature of the core flow has fallen to the surrounding temperature down-stream.
For better understanding of the construction ofthe device 5, it is advantageous to make use of Fig. 2 and 3 simultaneously. Furthermore, in order to prevent the individual figures becoming unnecessarily compli-cated, partial aspects of this device are distributedbetween the indivldual figures, reference being made to this fact, as needed, during the description of the embodiment example.
The core body of the device 5 shown in Fig. 2 con-sists of two half hollow partial conical bodies 11, 12which are located one upon the other, offset relative to one another. The offset of the respective center lines frees one tangential air inlet slot llc, 12c (Fig. 3) on each of the two sides in an axially symmetrical arrangement. The pre-compressed air 16, already mentioned above, flows through these slots into the internal space 13 of the device 5, i.e. into the conical hollow space. The conical shape of the partial conical bodies 11, 12 shown has a certain constant angle in the flow direction~ The partial conical bodies 11, 12 can, of course, describe an increasing cone angle (convex shape = trumpet shape) or a decreasing cone angle (concave shape = tulip shape) in the flow direction. The two shapes last mentioned are not recorded in the drawing because they can be imagined without difficulty. The shape which is finally used depends on the various parameters of the basic process. The shape shown in the drawing is preferably used. The tangential width of the air inlet slot3 llc, 12c is a dimension which results from the offset between the two center lines llb, 12b (see Fig. 3). The two partial conical bodies 11, 12 each have an initial cylindrical part lla, 12a which, by ~2/~31 analogy with the partial conical ~odies 11, 12, extend 2 offset relative to one another so that the tangential air inlet slots llc~ 12c are present over the whole length of the device 5. The double-cone device 5 can, S of course, be configured to be purely conical, i.e.
without an initial cylindrical part. A nozzle 14, which undertakes water spraying into the internal space 13 of the device 5, is accommodated in this initial cylindrical part. The spraying of water ensures that the pre-compressed air 16, which flows via inlet passages 17a, 17b (see Fig. 3) and through the tangential air inlet slots llc, 12c into the internal space 13 of the device 5, is continuously subjected to a cooling process. The introduction of the water quantity required into the internal space 13 of the device can take place in many ways. As an example, conduits ~not shown) can be provided in the region of the tangential air inlet slots llc, 12c as a support for or as a replacement for the spraying of water at the end, these conduits extending over the complete length of the double-cone device 5 and having, along -their length, a number of openings through which the required water can be introduced. Owing to the tangential flow of the air 16 into the internal space 13 of the device 5, a swirl motion oriented in the axial direction occurs and, because of its nature, this is suitable for producing thorough mixing with the second medium sprayed in (in our case, this is a conical water-spray pattern 15) which evaporates and so causes cooling. It should be noted that the vortex flow has intrinsically little swirl in the center but it has a surplus of axial velocity. Because the swirl rate increases strongly in the axial direction and reaches the critical value, the so-called breakdown value, at the end of the device 5, this provides in each region a vortex reverse flow 20 whose position is stable. This vortex reverse flow 20 ensures that the possibly surplus water, which is sprayed into the 92/0~1 ~ internal space 13 through the nozzle 14 and which, for ~ ~ 7 ~ ~
whatever reason, is not completely evaporated, is ~1 centrifuged out in the vortex plane 21. Other means of centrifuging out the water not evaporated can also be provided, which means are to be placed in the intermediate space la, downstream of the double-cone device 5 and upstream of the high-pressure compressor 8. The termination of the intercooler body is ~o~ned by a wall 19 which forms the inlet front of the annular chamber 10 along which the double-cone devices 5 provided are attached.
I'Obviously, numerous modification3 and variations of the present invention are possible in light of the above teachings. It ls therefore to be understood that within the scope of the appended claims, the invention may be practised otherwise than as specifically described herein."
.
Claims (6)
1. A compressor group of a gas turbine group, essentially comprising a first compression stage, an intercooler acting downstream of the first compression stage and a second compression stage acting downstream of the intercooler, wherein the intercooler is placed between the first compression stage and the second compression stage within the stator casing and in the flow direction, wherein the intercooler comprises at least one device which can be operated with water and through which the pre-compressed air can flow.
2. The compressor group as claimed in claim 1, wherein the device comprises at least two hollow conical partial bodies positioned one upon the other in the flow direction, the longitudinal axes of symmetry of which partial bodies extend radially offset relative to one another in such a way that opposed tangential air inlet slots for an airflow occur over the length of the device, wherein at least one nozzle which can be operated with water is present in an internal space formed by the partial conical bodies or in its region.
3. The compressor group as claimed in claim 2, wherein the partial bodies open out in the flow direction at a constant angle.
4. The compressor group as claimed in claim 2, wherein the cone angle of the partial bodies increases in the flow direction.
5. The compressor group as claimed in claim 2, wherein the cone angle of the partial bodies decreases in the flow direction.
6. A method of operating a compressor group as claimed in claims 1, 2, wherein water is sprayed into the internal space of the device, wherein this water comes into direct communication with the airflow and cools the latter by evaporation, wherein the water which does not evaporate is separated at the outlet from the device in the region of a vortex reverse flow zone forming there.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP92104491.3 | 1992-03-16 | ||
| EP92104491A EP0561011A1 (en) | 1992-03-16 | 1992-03-16 | Intercooled compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2091231A1 true CA2091231A1 (en) | 1993-09-17 |
Family
ID=8209436
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA 2091231 Abandoned CA2091231A1 (en) | 1992-03-16 | 1993-03-08 | Compressor group |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0561011A1 (en) |
| JP (1) | JPH0610702A (en) |
| CA (1) | CA2091231A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7093450B2 (en) | 2002-06-04 | 2006-08-22 | Alstom Technology Ltd | Method for operating a compressor |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2877098B2 (en) | 1995-12-28 | 1999-03-31 | 株式会社日立製作所 | Gas turbines, combined cycle plants and compressors |
| USRE39092E1 (en) * | 1997-06-30 | 2006-05-09 | Hitachi, Ltd. | Gas turbine with water injection |
| USRE38831E1 (en) | 1997-06-30 | 2005-10-18 | Hitachi, Ltd. | Gas turbine having water spray injection control |
| SG104914A1 (en) | 1997-06-30 | 2004-07-30 | Hitachi Ltd | Gas turbine |
| US20130139517A1 (en) | 2010-08-27 | 2013-06-06 | Hitachi, Ltd. | Solar Assisted Gas Turbine System |
| EP2818665A4 (en) | 2012-02-24 | 2016-03-23 | Mitsubishi Hitachi Power Sys | Solar heat assisted gas turbine system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR995131A (en) * | 1949-07-22 | 1951-11-28 | Rateau Soc | Development of two-flow turbo-reactors |
| DE2413507A1 (en) * | 1974-03-20 | 1975-10-02 | Motoren Turbinen Union | GAS TURBINE FOR CRYOGENIC FUEL |
| DE2925091A1 (en) * | 1979-06-21 | 1981-01-08 | Vinko Dipl Ing Mucic | Open cycle gas turbine engine - has water and fuel injected in stages to give isothermal compression and expansion |
| CH674561A5 (en) * | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie |
-
1992
- 1992-03-16 EP EP92104491A patent/EP0561011A1/en not_active Withdrawn
-
1993
- 1993-03-08 CA CA 2091231 patent/CA2091231A1/en not_active Abandoned
- 1993-03-16 JP JP5055297A patent/JPH0610702A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7093450B2 (en) | 2002-06-04 | 2006-08-22 | Alstom Technology Ltd | Method for operating a compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0610702A (en) | 1994-01-18 |
| EP0561011A1 (en) | 1993-09-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4928479A (en) | Annular combustor with tangential cooling air injection | |
| US8572982B2 (en) | Diffuser having distribution element for providing part-flow | |
| US5163285A (en) | Cooling system for a gas turbine | |
| US6672072B1 (en) | Pressure boosted compressor cooling system | |
| US4891936A (en) | Turbine combustor with tangential fuel injection and bender jets | |
| US4478553A (en) | Isothermal compression | |
| JP3811502B2 (en) | Gas turbine blades with cooling platform | |
| US4818178A (en) | Process for cooling the blades of thermal turbomachines | |
| US6742783B1 (en) | Seal segment for a turbine | |
| US7104749B2 (en) | Intake silencer for gas turbines | |
| US7685827B2 (en) | Gas turbine cooling systems and methods of assembly | |
| RU2303149C2 (en) | Gas-turbine engine (versions) and method of cooling of parts arranged inside | |
| US4291531A (en) | Gas turbine engine | |
| JPH0396628A (en) | Cooling gas turbine engine by steam | |
| US5632141A (en) | Diffuser with controlled diffused air discharge | |
| KR20020017913A (en) | Gas only nozzle fuel tip and method for cooling the same | |
| CN1270066C (en) | Gas turbine and method for operating gas turbine | |
| JP2005511947A (en) | Method and apparatus for increasing the power of a gas turbine using wet compression | |
| US3631674A (en) | Folded flow combustion chamber for a gas turbine engine | |
| US5109671A (en) | Combustion apparatus and method for a turbine engine | |
| CA2091231A1 (en) | Compressor group | |
| DK0578048T3 (en) | Cylindrical combustion chamber housing for a gas turbine | |
| RU2196239C2 (en) | Turbojet engine turbine cooling system | |
| JPS5969626A (en) | Liner for combustion device | |
| US4884746A (en) | Fuel nozzle and improved system and method for injecting fuel into a gas turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Dead |