US20100003123A1 - Inlet air heating system for a gas turbine engine - Google Patents
Inlet air heating system for a gas turbine engine Download PDFInfo
- Publication number
- US20100003123A1 US20100003123A1 US12/165,800 US16580008A US2010003123A1 US 20100003123 A1 US20100003123 A1 US 20100003123A1 US 16580008 A US16580008 A US 16580008A US 2010003123 A1 US2010003123 A1 US 2010003123A1
- Authority
- US
- United States
- Prior art keywords
- inlet
- exhaust
- gas
- turbine engine
- set forth
- 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
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
-
- 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
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
- F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
- F02C1/08—Semi-closed cycles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/08—Purpose of the control system to produce clean exhaust gases
- F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
Definitions
- the present invention relates generally to gas turbine engines and more particularly to an inlet air heating system of the engine and method of operating the same.
- Gas turbine engines are known, and typically include an inlet through which air passes to a compressor section. The air is compressed in the compressor section and passed downstream into a combustion section. In the combustion section, air is mixed with fuel and burned. Products of this combustion pass downstream across turbine rotors, to drive the rotors. A good deal of control is included in modern gas turbine engines.
- Inlet bleed heat involves bleeding off compressor discharge air and injecting it into the inlet air passing into the gas turbine engine. This heat increases inlet air temperature and reduces the power provided by the gas turbine engine. The use of the bleed air reduces the power in that as the inlet temperature increases, the provided power decreases. Unfortunately, bleeding off compressor discharge air reduces engine efficiency.
- a gas turbine engine has an inlet for delivering air into a compressor section.
- the compressor section is connected to feed air into a combustion section, where the air mixes with fuel and combusts.
- the combustion section is connected to turbine rotors such that products of combustion can pass over the turbine rotors to drive the turbine rotors.
- An exhaust communicates with the turbine sections to receive the products of combustion.
- a bleed tap communicates the exhaust to the inlet.
- a control controls the amount of exhaust gasses tapped into the inlet to achieve desired operating conditions without a loss in engine efficiency. Also, an inventive method and a system for reducing the power from a gas turbine engine are claimed.
- FIG. 1 is a schematic view of a gas turbine engine incorporating a unique inlet air heating system.
- FIG. 2 shows a second embodiment
- a gas turbine engine 20 is illustrated in FIG. 1 .
- An inlet 22 delivers air to a low pressure compressor section 24 , and downstream to a high pressure compressor section 26 .
- Air from the compressor section 26 passes into a combustion section 27 , and is mixed with fuel and burned.
- the combustion section 27 is of a dry low NOx premix (DLN) type wherein fuel and air are premixed prior to combustion to assure flame temperatures are kept uniformly low to prevent formation of NOx.
- Products of this combustion pass over a high pressure turbine 28 , and a low pressure turbine 30 , driving the turbine rotors 128 and 130 .
- the turbine rotors in turn drive compressor rotor 126 and compressor rotor 124 , respectively.
- a tap line 34 taps a portion of the exhaust gas through a blower 36 , and into a tap line 38 .
- the tap line 38 bleeds gas into inlet 22 in controlled amounts.
- the present invention also extends to engines including a fan located upstream of the compressor sections 26 , 24 .
- the amount of gas bled into the inlet 22 is controlled to achieve a desired amount of power to be delivered from the turbine sections 28 and 30 . As shown schematically in FIG. 1 , the turbine sections 28 and 30 deliver power to a generator 40 .
- blower 36 may not be necessary.
- blower 36 may not be necessary.
- a simple damper 42 as shown schematically in FIG. 2 , may be sufficient.
- the damper is rotated under the control of a motor 44 to control the amount of air delivered from exhaust 32 to inlet 22 .
- the exhaust gasses may have corrosive materials produced when burning fuel.
- the material and coatings of the turbine sections 28 and 30 , and even perhaps the compressor sections 24 and 26 should be selected to resist any potential corrosion issues.
- the temperature of the inlet air can be increased, and the oxygen content reduced. Reducing the oxygen content may further reduce NOx emissions.
- a worker of ordinary skill in this art would recognize how much air to deliver from the exhaust 32 to the inlet 22 dependent upon the relative temperatures at the two locations preferably measured by sensor 39 and sensor 41 , respectively.
- Sensors 39 , 41 send signals to a control 43 for the blower motor 36 , or the damper motor 44 .
- Control 43 can be any appropriate processor.
- Dependent on the desired temperature, and operating temperature, the air delivered to the compressor 24 can be between zero and twenty percent exhaust gas.
- tap lines 34 and 38 can be connected to existing gas turbine engines.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Control Of Turbines (AREA)
Abstract
Description
- The present invention relates generally to gas turbine engines and more particularly to an inlet air heating system of the engine and method of operating the same.
- Gas turbine engines are known, and typically include an inlet through which air passes to a compressor section. The air is compressed in the compressor section and passed downstream into a combustion section. In the combustion section, air is mixed with fuel and burned. Products of this combustion pass downstream across turbine rotors, to drive the rotors. A good deal of control is included in modern gas turbine engines.
- One recent advancement in gas turbine engines is the so-called dry low NOx or “DLN” combustion systems. These are often utilized in industrial gas turbine engines to achieve very low levels of NOx emissions, without any need for water injection. These engines typically have a very narrow operating range over which emissions are kept low.
- One way to increase the operating range is a concept known as inlet bleed heat. Inlet bleed heat involves bleeding off compressor discharge air and injecting it into the inlet air passing into the gas turbine engine. This heat increases inlet air temperature and reduces the power provided by the gas turbine engine. The use of the bleed air reduces the power in that as the inlet temperature increases, the provided power decreases. Unfortunately, bleeding off compressor discharge air reduces engine efficiency.
- A gas turbine engine has an inlet for delivering air into a compressor section. The compressor section is connected to feed air into a combustion section, where the air mixes with fuel and combusts. The combustion section is connected to turbine rotors such that products of combustion can pass over the turbine rotors to drive the turbine rotors. An exhaust communicates with the turbine sections to receive the products of combustion. A bleed tap communicates the exhaust to the inlet. A control controls the amount of exhaust gasses tapped into the inlet to achieve desired operating conditions without a loss in engine efficiency. Also, an inventive method and a system for reducing the power from a gas turbine engine are claimed.
- These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
-
FIG. 1 is a schematic view of a gas turbine engine incorporating a unique inlet air heating system. -
FIG. 2 shows a second embodiment. - A
gas turbine engine 20 is illustrated inFIG. 1 . Aninlet 22 delivers air to a lowpressure compressor section 24, and downstream to a highpressure compressor section 26. Air from thecompressor section 26 passes into acombustion section 27, and is mixed with fuel and burned. Preferably, thecombustion section 27 is of a dry low NOx premix (DLN) type wherein fuel and air are premixed prior to combustion to assure flame temperatures are kept uniformly low to prevent formation of NOx. Products of this combustion pass over ahigh pressure turbine 28, and alow pressure turbine 30, driving theturbine rotors drive compressor rotor 126 andcompressor rotor 124, respectively. Downstream of the turbine sections the products of combustion pass into anexhaust 32. As shown, atap line 34 taps a portion of the exhaust gas through ablower 36, and into atap line 38. Thetap line 38 bleeds gas intoinlet 22 in controlled amounts. Although no fan section is shown, the present invention also extends to engines including a fan located upstream of thecompressor sections - The amount of gas bled into the
inlet 22 is controlled to achieve a desired amount of power to be delivered from theturbine sections FIG. 1 , theturbine sections generator 40. - In some applications, if the pressure difference between the
exhaust 32 and theinlet 22 is sufficient,blower 36 may not be necessary. As an example, if a heat recovery steam boiler is included, the pressure difference might be sufficient. Instead, asimple damper 42, as shown schematically inFIG. 2 , may be sufficient. As should be appreciated, the damper is rotated under the control of amotor 44 to control the amount of air delivered fromexhaust 32 toinlet 22. - Notably, the exhaust gasses may have corrosive materials produced when burning fuel. Thus, with this system bleeding air from the exhaust through the
lines turbine sections compressor sections - By recirculating gas from the
exhaust 32 to theinlet 22, the temperature of the inlet air can be increased, and the oxygen content reduced. Reducing the oxygen content may further reduce NOx emissions. - A worker of ordinary skill in this art would recognize how much air to deliver from the
exhaust 32 to theinlet 22 dependent upon the relative temperatures at the two locations preferably measured bysensor 39 and sensor 41, respectively.Sensors 39, 41 send signals to acontrol 43 for theblower motor 36, or thedamper motor 44.Control 43 can be any appropriate processor. Dependent on the desired temperature, and operating temperature, the air delivered to thecompressor 24 can be between zero and twenty percent exhaust gas. - Also, the
tap lines blower motor 36, ordamper 42, can be connected to existing gas turbine engines. - Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims (15)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/165,800 US20100003123A1 (en) | 2008-07-01 | 2008-07-01 | Inlet air heating system for a gas turbine engine |
EP09250925A EP2141335B1 (en) | 2008-07-01 | 2009-03-30 | An inlet air heating system for a gas turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/165,800 US20100003123A1 (en) | 2008-07-01 | 2008-07-01 | Inlet air heating system for a gas turbine engine |
Publications (1)
Publication Number | Publication Date |
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US20100003123A1 true US20100003123A1 (en) | 2010-01-07 |
Family
ID=41136885
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/165,800 Abandoned US20100003123A1 (en) | 2008-07-01 | 2008-07-01 | Inlet air heating system for a gas turbine engine |
Country Status (2)
Country | Link |
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US (1) | US20100003123A1 (en) |
EP (1) | EP2141335B1 (en) |
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