Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids

Title: Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids

A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an ambient air cooling system, and the high pressure cooling system may be a compressor bleed air cooling system. In at least one embodiment, the compressor bleed air cooling system in communication with a high pressure subsystem that may be a snubber cooling system positioned within a snubber. A delivery system including a movable air supply tube may be used to separate the low and high pressure cooling subsystems. The delivery system may enable high pressure cooling air to be passed to the snubber cooling system separate from low pressure cooling fluid supplied by the low pressure cooling system to other portions of the turbine airfoil cooling system.

Inventors:: Marsh, Jan H.; Messmann, Stephen John; Scribner, Carmen Andrew

Issue Date:: 2017-10-25

OSTI Identifier:: 1404936

Assignee:: SIEMENS ENERGY, INC. NETL

Patent Number(s):: 9,797,259

Application Number:: 14/200,168

Contract Number:: FC26-05NT42644

Resource Relation:: Patent File Date: 2014 Mar 07

Research Org:: SIEMENS ENERGY, INC. Orlando, FL (United States)

Sponsoring Org:: USDOE

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING

Full Text
View Full Text

Have feedback or suggestions for a way to improve these results? !

Save / Share this Record no
Export Metadata
- Endnote
- RIS
- Excel
- CSV
- XML
Send to Email

Send to Email

Email address:

Content:

Works referenced in this record:

Gas Turbine Rotor Assembly
patent, April 1960

Hyde, J.A.C.
US Patent Document 2,931,623
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F2931623

Airfoil with dual source cooling
patent, March 1996

Pighetti, Annette; Seidel, Lawrence
US Patent Document 5,498,126
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F5498126

Gas turbine moving blade steam cooling system
patent, October 1999

Uematsu, Kazuo; Chikami, Rintaro; Tomita, Yasuoki
US Patent Document 5,971,707
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F5971707

Dual cooled shroud
patent, November 1999

Liotta, Gary; Acquaviva, Paul
US Patent Document 5,993,150
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F5993150

Combustion turbine cooling media supply system and related method
patent, May 2002

Priestley, Robert
US Patent Document 6,389,793
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F6389793

Method and apparatus for cooling high temperature components in a gas turbine
patent, December 2002

Chen, Allen; Horazak, Dennis
US Patent Document 6,487,863
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F6487863

Dual coolant turbine blade
patent, November 2005

Lee, Ching-Pang
US Patent Document 6,960,060
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F6960060

Part load blade tip clearance control
patent, November 2005

Little, David
US Patent Document 6,968,696
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F6968696

Modulated flow turbine nozzle
patent, March 2006

Orlando, Robert; Moniz, Thomas; Brauer, John
US Patent Document 7,007,488
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7007488

Blade and disk radial pre-swirlers
patent, March 2007

Girgis, Sami; Marini, Remo
US Patent Document 7,189,056
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7189056

Turbine blade with vibration damper
patent, September 2007

Garner, Chad
US Patent Document 7,270,517
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7270517

Integrated turbine sealing air and active clearance control system and method
patent, November 2007

Leach, David; Beadie, Douglas; Nigmatulin, Tagir
US Patent Document 7,293,953
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7293953

Methods and apparatus for cooling gas turbine rotor blades
patent, April 2009

Itzel, Gary; Jacala, Ariel; Lewis, Doyle
US Patent Document 7,513,738
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7513738

Turbine last stage blade with forced vortex driven cooling air
patent, March 2010

Brostmeyer, Joseph; Wilson, Jack
US Patent Document 7,677,048
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7677048

Compound turbine cooled engine
patent, June 2010

Lee, Ching-Pang; Moniz, Thomas; Orlando, Robert
US Patent Document 7,743,613
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7743613

Interstage cooled turbine engine
patent, January 2011

Lee, Ching-Pang; Moniz, Thomas; Orlando, Robert
US Patent Document 7,870,742
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7870742

Compound nozzle cooled engine
patent, January 2011

Lee, Ching-Pang; Moniz, Thomas; Orlando, Robert
US Patent Document 7,870,743
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7870743

Dual interstage cooled engine
patent, April 2011

Lee, Ching-Pang; Moniz, Thomas; Orlando, Robert
US Patent Document 7,926,289
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F7926289

Turbine blade with single tip rail with a mid-positioned deflector portion
patent, April 2012

Liang, George
US Patent Document 8,157,505
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F8157505

Gas turbine blade with double impingement cooled single suction side tip rail
patent, May 2012

Liang, George
US Patent Document 8,172,507
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F8172507

Turbine blade squealer tip rail with fence members
patent, November 2012

Little, David
US Patent Document 8,313,287
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=%2Fnetahtml%2FPTO%2Fsearch-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN%2F8313287

Snubber Assembly for Turbine Blades
patent-application, August 2011

Marra, John J.
US Patent Application 12/701041; 20110194939
URL: http://appft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PG01&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.html&r=1&f=G&l=50&s1=%2220110194939%22.PGNR.&OS=DN/20110194939&RS=DN/20110194939

Cooled Snubber Structure for Turbine Blades
patent-application, August 2011

Mayer, Clinton A.; Campbell, Christian X.; Whalley, Andrew
US Patent Application 13/023651; 20110194943
URL: http://appft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PG01&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.html&r=1&f=G&l=50&s1=%2220110194943%22.PGNR.&OS=DN/20110194943&RS=DN/20110194943

Bicast Turbine Engine Components
patent-application, February 2014

Messmann, Stephen John; Campbell, Christian X.; James, Allister William
US Patent Application 14/071687; 20140056716
URL: http://appft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PG01&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.html&r=1&f=G&l=50&s1=%2220140056716%22.PGNR.&OS=DN/20140056716&RS=DN/20140056716

Bucket Assembly for Use in a Turbine Engine
patent-application, April 2015

Pierre, Sylvain; Brown, Holly Davis
US Patent Application 14/066928; 20150118062
URL: http://appft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PG01&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.html&r=1&f=G&l=50&s1=%2220150118062%22.PGNR.&OS=DN/20150118062&RS=DN/20150118062

Similar Records

Similar records in DOepatents and OSTI.GOV collections:

Apparatus and methods of reheating gas turbine cooling steam and high pressure steam turbine exhaust in a combined cycle power generating system

Patent Tomlinson, Leroy Omar ; Smith, Raub Warfield

In a combined cycle system having a multi-pressure heat recovery steam generator, a gas turbine and steam turbine, steam for cooling gas turbine components is supplied from the intermediate pressure section of the heat recovery steam generator supplemented by a portion of the steam exhausting from the HP section of the steam turbine, steam from the gas turbine cooling cycle and the exhaust from the HP section of the steam turbine are combined for flow through a reheat section of the HRSG. The reheated steam is supplied to the IP section inlet of the steam turbine. Thus, where gas turbinemore »« less
Full Text Available January 2002
Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine

Patent Lee, Ching-Pang ; Myers, Caleb ; Johnson, Erik ; Koester, Steven

An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channelmore »« less
Full Text Available August 2018
Low pressure cooling seal system for a gas turbine engine

Patent Marra, John J

A low pressure cooling system for a turbine engine for directing cooling fluids at low pressure, such as at ambient pressure, through at least one cooling fluid supply channel and into a cooling fluid mixing chamber positioned immediately downstream from a row of turbine blades extending radially outward from a rotor assembly to prevent ingestion of hot gases into internal aspects of the rotor assembly. The low pressure cooling system may also include at least one bleed channel that may extend through the rotor assembly and exhaust cooling fluids into the cooling fluid mixing chamber to seal a gap betweenmore »« less
Full Text Available April 2014
Turbine airfoil with an internal cooling system having vortex forming turbulators

Patent Lee, Ching-Pang

A turbine airfoil usable in a turbine engine and having at least one cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The configuration of turbulators may create a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demandmore » and better turbine performance.« less
Full Text Available December 2014
Turbine airfoil with ambient cooling system

Patent Campbell, Jr, Christian X. ; Marra, John J. ; Marsh, Jan H.

A turbine airfoil usable in a turbine engine and having at least one ambient air cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels configured to receive ambient air at about atmospheric pressure. The ambient air cooling system may have a tip static pressure to ambient pressure ratio of at least 0.5, and in at least one embodiment, may include a tip static pressure to ambient pressure ratio of between about 0.5 and about 3.0. The cooling system may also be configured such that an under root slot chamber inmore »« less
Full Text Available June 2016