Processing

Please wait...

Settings

Settings

1. WO1996002804 - PRIMARY SURFACE HEAT EXCHANGER FOR USE WITH A HIGH PRESSURE RATIO GAS TURBINE ENGINE

Publication Number WO/1996/002804
Publication Date 01.02.1996
International Application No. PCT/US1995/007081
International Filing Date 05.06.1995
IPC
F28D 9/00 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
28HEAT EXCHANGE IN GENERAL
DHEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT; HEAT STORAGE PLANTS OR APPARATUS IN GENERAL
9Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
CPC
F28D 9/0037
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
28HEAT EXCHANGE IN GENERAL
DHEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
9Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
0031the conduits for one heat-exchange medium being formed by paired plates touching each other
0037the conduits for the other heat-exchange medium also being formed by paired plates touching each other
F28F 2250/104
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
28HEAT EXCHANGE IN GENERAL
FDETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
2250Arrangements for modifying the flow of the heat exchange media
10Particular pattern of flow of the heat exchange media
104with parallel flow
Y10S 165/356
YSECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
10TECHNICAL SUBJECTS COVERED BY FORMER USPC
STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
165Heat exchange
355having separate flow passage for two distinct fluids
356Plural plates forming a stack providing flow passages therein
Applicants
  • SOLAR TURBINES INCORPORATED [US/US]; 2200 Pacific Highway P.O. Box 85376 San Diego, CA 92186-5376, US
Inventors
  • DARRAGH, Charles, T.; US
  • HOLMAN, Leonard; US
  • LUCKETT, Thomas, M.; US
  • WARD, Michael, E.; US
Agents
  • CAIN, Larry, G. ; 100 N.E. Adams Street Peoria, IL 61629-6490, US
Priority Data
08/274,87914.07.1994US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) PRIMARY SURFACE HEAT EXCHANGER FOR USE WITH A HIGH PRESSURE RATIO GAS TURBINE ENGINE
(FR) SURFACE PRIMAIRE D'ECHANGEUR THERMIQUE POUR MOTEUR A TURBINE A GAZ A TAUX DE COMPRESSION ELEVE
Abstract
(EN)
Prior art recuperators or heat exchangers have been restricted in use to only part speed and power application when adapted for use with high pressure gas turbine engine. The present recuperator or heat exchanger (12) has been adapted for use with a high pressure ratio gas turbine engine (10). The recuperator (12) includes a plurality of air cells (44) being formed by a plurality of primary surface sheets (46). The primary surface sheets (46) define a first surface (48) and a second surface (50) and has a plurality of corrugations (58) formed therein. Each of the plurality of corrugations (58) has a crest (60) and a root (62) extending from the respective first surface (48) and second surface (50) a preestablished axial distance. The preestablished axial distance from the crest (60) to the first surface (48) being unequal to that of the preestablished axial distance from the root (62) to the second surface (50).
(FR)
Les récupérateurs ou échangeurs thermiques selon les états antérieurs de la technique n'ayant pas été utilisés au maximum des possibilités, en ce qui concerne tant la vitesse que l'énergie dans le cas des moteurs à turbine à gaz haute pression, le récupérateur ou échangeur thermique (12) de la présente invention a été adapté pour une utilisation sur un moteur à turbine à gaz à taux de compression élevé (10). Le récupérateur (12) comporte une pluralité de cellules d'air (44) constituées d'une pluralité de feuilles de surface primaire (46). Ces feuilles de surface primaire (46) définissant une 1ère surface (48) et une 2ème surface (50) présentent une pluralité d'ondulations (58) formées dans la feuille. Chacune des pluralités d'ondulations (58) présente un saillant (60) et un fond (62) déterminant une distance axiale préétablie entre leurs 1ères surfaces (48) et 2èmes surfaces (50) respectives. La distance axiale préétablie entre le saillant (60) et la 1ère surface est différente de la distance axiale préétablie entre le fond (62) et la 2ème surface (50).
Latest bibliographic data on file with the International Bureau