US2438635A - Turbine system utilizing hot driving gases - Google Patents
Turbine system utilizing hot driving gases Download PDFInfo
- Publication number
- US2438635A US2438635A US501101A US50110143A US2438635A US 2438635 A US2438635 A US 2438635A US 501101 A US501101 A US 501101A US 50110143 A US50110143 A US 50110143A US 2438635 A US2438635 A US 2438635A
- Authority
- US
- United States
- Prior art keywords
- air
- combustion
- gases
- turbine
- turbine system
- 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.)
- Expired - Lifetime
Links
- 239000007789 gas Substances 0.000 title description 13
- 238000002485 combustion reaction Methods 0.000 description 19
- 239000000047 product Substances 0.000 description 11
- 239000000446 fuel Substances 0.000 description 10
- 238000010438 heat treatment Methods 0.000 description 10
- 239000000567 combustion gas Substances 0.000 description 5
- 239000003245 coal Substances 0.000 description 3
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000003303 reheating Methods 0.000 description 1
- 239000012265 solid product Substances 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Images
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
- 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
- F02C1/05—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
- F02C1/06—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy using reheated exhaust gas
Definitions
- This invention relates to turbine systems and particularly to systems utilizing hot driving gases.
- systems may be provided in which not only are products of combustion excluded from the turbines, which are operated with highly heated air as the motive fluid, but the entire air exhausted from the turbines will pass to the combustion chamber or chambers to secure the most effective utilization of all of the heat energy available.
- Fig. 1 isa diagram showing one system providedA in accordance with the present invention.
- Fig. 2 is similar diagram but showing the addition of heat between turbine stages.
- combustion chambers 32 and 34 into which fuel is introduced respectively at 36 and 38 to be burned ,in air admitted thereto, as hereinafter described.
- the combustion chambers may take forms of highly varying nature, depending upon the fuel which is burned. If the fuel is oil or gas, it may be injected in the form of a jet or spray. Ii the fuel is finely powdered coal, it may be similarly injected in dispersed form.
- the combustion chamber may involve the introduction of coal or other solid fuel in relatively large pieces, in which case a stoker may be used.
- the products of combustion frm the chamber 34 pass through an initial portion 40 of the passages in the heat exchanger 42.
- the products of combustion from 32 mingle with the products of combustion from 3l through Claims. (Cl. 60-59) later portions 44 of the combustion gas passages in the heat exchanger.
- the air is compressed by the centrifugal compressors 38 and 50 and. after receiving heat, drives, in series, the turbines 52, 56, and SEL
- the air exhausted from the last turbine passes through the connections 58 and to the respective combustion chambers.
- Fig. 2 shows a modication, in which re-heating of air between stages is eected.
- a single combustion chamber B2 is provided receiving fuel at 6d and air from the last stage turbine.
- the products of combustion are in this case split, with a major portion owing through the connection BS to the initial gas passages l of the heat exchanger 63.
- Some of the combustion gases are diverted at l2 to a heat exchanger 1d. passing through the passage or passages 16 thereof and thence through connection 'it to mingle with the combustion gases passing through l@ in the heat exchanger 68, and with them passing through a'further portion of the gas passages indicated at 3G.
- Another portion of the combustion gases is diverted at 82 to the passages 84 of the heat exchanger 8i, from which the gases iiow through 88 to mingle with the other combustion gases to pass with them through the latter portions 90 of the heat exchanger passages.
- the air is compressed by the two compressor stages 92 and 94 and passes, as indicated at 96, in heat exchange with the gases flowing through the heat exchanger.
- the heated air passes from 68 to the high pressure turbine 98, whence it flows through the passages
- the efliciency may be increased, inasmuch as the eiilciency of a gas turbine increases rapidly with rise of temperature.
- a turbine system comprising a plurality of aesaeso' turbines arranged in series. means ior cmpressing air driven by at least one of the turbines, means for heating the air. means for directing the heated air to the turbines to drive the same, and means for burning fuel in air exhausted from the turbines, the means for heating the air utilizing the products of said combustion, said means for heating the air involving an air passage. means for subjecting the air in counterow arrangement to heat exchange with one stream of said products of combustion and means for adding to said stream at an intermediate point thereof an additional stream of said priiucts of combustion.
- a turbine system comprising a plurality of turbines arranged in series, means for compressing air driven by at least one of the turbines, means for heating the air, means for directing the heated air to the turbines to drive the same, means for burning fuel in air exhausted from the turbines, the means for heating the air utilizing the products of said combustion. and means for reheating the air between turbine stages', said means for heating the air involving an air passage. means for subjecting the air in countermeans.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- High Energy & Nuclear Physics (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air Supply (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Description
MalCh 30, 1948. J4. s. HAvERsrlc/:K 2,438,535
TURBINE SYSTEM UTILIZlNG HOT DRIVING GASES Mil-fdl 30, 1948 J. s. HAvERsTlcK V 2,438,635
` TURBINE SYSTEM UTILIZ-ING HOT DRIVING GASES Filed Sept. 3, 1943 2 Sheets-Sheet 2 /47 afm/Ki Patented Mar. 3.0, 1948 TURBINE SYSTEM UTILIZING HOT DRIVING GASES John s. naversuek, Trenton, N. J., assigns: to ne Laval Steam Turbine Company, Trenton, N. J a corporation of New Jersey Application September 3, 1943, Serial No. 501,101
This invention relates to turbine systems and particularly to systems utilizing hot driving gases.
-In the usual arrangement for driving a turbine by means of gases at high temperature, the air is rst compressed, passed through a heat exchanger to receive heat from exhaust gases, and introduced into a combustion chamber in which fuel is burned therein. The products of combustion are then passed through one or more turbines and exhausted through the heat exchanger to pre-heat the compressed air. A serious drawback in any such system is that the products of combustion must pass through the turbine or turbines, wherein they may cause both corrosion and erosion with the result that only high grade fuels may be used, the use of coal, which gives rise to solid products, or the use of low grade fuels, which give rise to highly corrosive products, being thereby precluded.
In accordance with the present invention, systems may be provided in which not only are products of combustion excluded from the turbines, which are operated with highly heated air as the motive fluid, but the entire air exhausted from the turbines will pass to the combustion chamber or chambers to secure the most effective utilization of all of the heat energy available.
The foregoing objects of the invention, as well as other objects relating to details of arrangement and operation, will be apparent from the following description read in conjunction with the accompanying drawings, in which:
Fig. 1 isa diagram showing one system providedA in accordance with the present invention; and
Fig. 2 is similar diagram but showing the addition of heat between turbine stages.
Referring rst to the modification of Fig. 1, there is illustrated therein two combustion chambers 32 and 34 into which fuel is introduced respectively at 36 and 38 to be burned ,in air admitted thereto, as hereinafter described. The combustion chambers may take forms of highly varying nature, depending upon the fuel which is burned. If the fuel is oil or gas, it may be injected in the form of a jet or spray. Ii the fuel is finely powdered coal, it may be similarly injected in dispersed form. On the other hand, the combustion chamber may involve the introduction of coal or other solid fuel in relatively large pieces, in which case a stoker may be used.
The products of combustion frm the chamber 34 pass through an initial portion 40 of the passages in the heat exchanger 42. The products of combustion from 32, on the other hand, mingle with the products of combustion from 3l through Claims. (Cl. 60-59) later portions 44 of the combustion gas passages in the heat exchanger. By reason of counterflow arrangement with the air passage or passages 46 there may be secured more effective heating of the air to a high temperature. The air is compressed by the centrifugal compressors 38 and 50 and. after receiving heat, drives, in series, the turbines 52, 56, and SEL The air exhausted from the last turbine passes through the connections 58 and to the respective combustion chambers.
Fig. 2 shows a modication, in which re-heating of air between stages is eected. In this modification, a single combustion chamber B2 is provided receiving fuel at 6d and air from the last stage turbine. The products of combustion are in this case split, with a major portion owing through the connection BS to the initial gas passages l of the heat exchanger 63. Some of the combustion gases are diverted at l2 to a heat exchanger 1d. passing through the passage or passages 16 thereof and thence through connection 'it to mingle with the combustion gases passing through l@ in the heat exchanger 68, and with them passing through a'further portion of the gas passages indicated at 3G.
Another portion of the combustion gases is diverted at 82 to the passages 84 of the heat exchanger 8i, from which the gases iiow through 88 to mingle with the other combustion gases to pass with them through the latter portions 90 of the heat exchanger passages.
The air is compressed by the two compressor stages 92 and 94 and passes, as indicated at 96, in heat exchange with the gases flowing through the heat exchanger. The heated air passes from 68 to the high pressure turbine 98, whence it flows through the passages |00 in the heat exchanger 14, in which its temperature is raised prior to its entering the intermediate stage turbine |02. From this the air passes for further re-heating ,through the passages |04 in the heat exchanger 86, from which in turn it enters the last stage turbine I 06 arranged to deliver power through the shaft |08. From |06 the exhaust air passes to the combustion chamber.
By reason of the re-heating between the stages in this modification, the efliciency may be increased, inasmuch as the eiilciency of a gas turbine increases rapidly with rise of temperature.
It will be clear that numerous changes may be made in detaik of the invention without departing from the scope thereof as defined in the following claims.
What is claimed is:
1. A turbine system comprising a plurality of aesaeso' turbines arranged in series. means ior cmpressing air driven by at least one of the turbines, means for heating the air. means for directing the heated air to the turbines to drive the same, and means for burning fuel in air exhausted from the turbines, the means for heating the air utilizing the products of said combustion, said means for heating the air involving an air passage. means for subjecting the air in counterow arrangement to heat exchange with one stream of said products of combustion and means for adding to said stream at an intermediate point thereof an additional stream of said priiucts of combustion.
2. A turbine system comprising a plurality of turbines arranged in series, means for compressing air driven by at least one of the turbines, means for heating the air, means for directing the heated air to the turbines to drive the same, means for burning fuel in air exhausted from the turbines, the means for heating the air utilizing the products of said combustion. and means for reheating the air between turbine stages', said means for heating the air involving an air passage. means for subjecting the air in countermeans.
JOHN S. HAVERSTICK.
REFERENCES CITED The following references are of record in the ille of this patent:
FOREIGN PATENTS Number Country Date 520,654 Germany Mar. 17, 1931 215,485
Switzerland Oct. 1,1941
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US501101A US2438635A (en) | 1943-09-03 | 1943-09-03 | Turbine system utilizing hot driving gases |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US501101A US2438635A (en) | 1943-09-03 | 1943-09-03 | Turbine system utilizing hot driving gases |
Publications (1)
Publication Number | Publication Date |
---|---|
US2438635A true US2438635A (en) | 1948-03-30 |
Family
ID=23992143
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US501101A Expired - Lifetime US2438635A (en) | 1943-09-03 | 1943-09-03 | Turbine system utilizing hot driving gases |
Country Status (1)
Country | Link |
---|---|
US (1) | US2438635A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3893300A (en) * | 1973-04-30 | 1975-07-08 | Nrg Inc | External combustion engine and engine cycle |
US5586429A (en) * | 1994-12-19 | 1996-12-24 | Northern Research & Engineering Corporation | Brayton cycle industrial air compressor |
US20050257523A1 (en) * | 2004-05-22 | 2005-11-24 | Proeschel Richard A | Afterburning, recuperated, positive displacement engine |
US20100300099A1 (en) * | 2009-05-27 | 2010-12-02 | Moxian Chen | Air-medium power system |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE520654C (en) * | 1927-09-24 | 1931-03-17 | Walter Baensch | Multi-stage open hot air rotary piston machine |
CH215485A (en) * | 1939-04-11 | 1941-06-30 | Jendrassik Georg | Gas turbine system equipped with a heat exchanger. |
-
1943
- 1943-09-03 US US501101A patent/US2438635A/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE520654C (en) * | 1927-09-24 | 1931-03-17 | Walter Baensch | Multi-stage open hot air rotary piston machine |
CH215485A (en) * | 1939-04-11 | 1941-06-30 | Jendrassik Georg | Gas turbine system equipped with a heat exchanger. |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3893300A (en) * | 1973-04-30 | 1975-07-08 | Nrg Inc | External combustion engine and engine cycle |
US5586429A (en) * | 1994-12-19 | 1996-12-24 | Northern Research & Engineering Corporation | Brayton cycle industrial air compressor |
US20050257523A1 (en) * | 2004-05-22 | 2005-11-24 | Proeschel Richard A | Afterburning, recuperated, positive displacement engine |
US7028476B2 (en) | 2004-05-22 | 2006-04-18 | Proe Power Systems, Llc | Afterburning, recuperated, positive displacement engine |
US20100300099A1 (en) * | 2009-05-27 | 2010-12-02 | Moxian Chen | Air-medium power system |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7600368B2 (en) | High compression gas turbine with superheat enhancement | |
US3971211A (en) | Thermodynamic cycles with supercritical CO2 cycle topping | |
US2268270A (en) | Gas turbine plant | |
US2461186A (en) | Gas turbine installation | |
US2428136A (en) | Combustion gas and waste heat steam turbine | |
US2633707A (en) | Compound plant for producing mechanical power and heating steam with gas and steam turbines | |
US2298663A (en) | Gas turbine plant | |
US2584232A (en) | Gas turbine power plant, including means to treat combustion products between successive stages of expansion | |
US2632297A (en) | Gas turbine plant | |
US3127744A (en) | Combined steam turbine-air turbine power plants | |
US6199363B1 (en) | Method for operating a gas turbogenerator set | |
US2438635A (en) | Turbine system utilizing hot driving gases | |
US2463964A (en) | Gas turbine plant employing makup air precompression for peak loads | |
RU2094636C1 (en) | Gas-turbine plant and its operating process (options) | |
US2464861A (en) | Hot-air turbine power plant | |
US3398525A (en) | Combined multistage power plant having a rotary compressor serving as the low pressure stage and a rotary pressure-wave machine serving as the high pressure stage | |
US2466723A (en) | Steam and gas power generating plant | |
US2419689A (en) | Gas turbine | |
JPS61201831A (en) | Power generation method | |
US2453938A (en) | Turbine thermal power plant using hot air as motivating fluid | |
US1901873A (en) | Multistage constant volume explosion process and apparatus | |
US2282740A (en) | Heat exchange system | |
US3420054A (en) | Combined steam-gas cycle with limited gas turbine | |
US1982664A (en) | Compound gas turbine and method of producing power therewith | |
US2613495A (en) | Vapor and gas power plant utilizing equipressure vapor generator |